Calculator A to Z

Calculators Created by Sanjay Krishna

Sanjay Krishna
Amrita School of Engineering (ASE), Vallikavu
https://www.linkedin.com/in/sanjay-krishna-80a7b913b/
299
Formulas Created
200
Formulas Verified
108
Across Categories

List of Calculators by Sanjay Krishna

Following is a combined list of all the calculators that have been created and verified by Sanjay Krishna. Sanjay Krishna has created 299 and verified 200 calculators across 108 different categories till date.
2 Layers (1)
Verified Interface Temperature of Composite Wall of 2 Layers given Outer Surface Temperature
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7 More 2 Layers Calculators
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Aero Thermal Dynamics (16)
Created Aerodynamic Heating to Surface
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Created Chapman-Rubesin Factor
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Created Coefficient of Friction using Stanton Equation for Incompressible Flow
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Created Density Calculation using Chapman-Rubesin Factor
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Created Internal Energy for Hypersonic Flow
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Created Non Dimensional Internal Energy Parameter
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Created Non Dimensional Internal Energy Parameter using Wall-to-Freestream Temperature Ratio
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Created Non Dimensional Static Enthalpy
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Created Stanton Equation using Overall Skin Friction Coefficient for Incompressible Flow
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Created Stanton Number for Incompressible Flow
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Created Static Density Calculation using Chapman-Rubesin Factor
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Created Static Enthalpy
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Created Static Viscosity Calculation using Chapman-Rubesin Factor
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Created Thermal Conductivity using Prandtl Number
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Created Viscosity Calculation using Chapman-Rubesin Factor
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Created Wall Temperature Calculation using Internal Energy Change
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Aerodynamic Measurements and Wind Tunnel Testing (1)
Verified Airspeed Measurement by Pitot Tube
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9 More Aerodynamic Measurements and Wind Tunnel Testing Calculators
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Aerodynamic Parameters (1)
Verified Sidewash angle
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10 More Aerodynamic Parameters Calculators
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Aircraft Dynamics Nomenclature (4)
Verified Velocity along Roll Axis for Small Sideslip Angle
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Verified Velocity along Yaw Axis for Small Angle of Attack
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Verified Yawing Moment
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Verified Yawing moment coefficient
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14 More Aircraft Dynamics Nomenclature Calculators
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Approximate Methods of Hypersonic Inviscid Flowfields (11)
Created Non-Dimensional Density
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Created Non-Dimensional Density for High Mach Number
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Created Non-Dimensional Parallel Velocity Component for High Mach Number
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Created Non-Dimensional Perpendicular Velocity Component for High Mach Number
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Created Non-Dimensional Pressure
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Created Non-Dimensional Pressure for High Mach Number
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Created Non-Dimensional Radius for Hypersonic Vehicles
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Created Slenderness Ratio with Cone Radius for Hypersonic Vehicle
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Created Transformed Conical Variable
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Created Transformed Conical Variable with Cone Angle in Hypersonic Flow
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Created Transformed Conical Variable with Wave Angle
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Approximate Results Applied to Hypersonic Vehicles (15)
Created Adiabatic Wall Enthalpy over Flat Plate using Stanton Number
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Created Coefficient of Drag over Flat under Freestream Flow Conditions
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Created Drag Force over Flat Plate
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Created Free Stream Enthalpy over Flat Plate with Freestream Conditions
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Created Free Stream Velocity over Flat Plate using Drag Force
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Created Free Stream Velocity over Flat Plate with Freestream Conditions
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Created Freestream Density over Flat Plate using Stanton Number
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Created Freestream Density over Flat under Freestream Flow Conditions
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Created Freestream Stanton Number for Flat Plate
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Created Freestream Velocity over Flat Plate using Stanton Number
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Created Local Heat Transfer over Flat Plate using Stanton Number
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Created Pressure Ratio for Insulated Flat Plate, Strong Interaction
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Created Pressure Ratio for Insulated Flat Plate, Weak Interaction
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Created Total Enthalpy over Flat Plate with Freestream Conditions
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Created Wall Enthalpy over Flat Plate using Stanton Number
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Bernoulli's Equation and Pressure Concepts (3)
Verified Pressure at Upstream Point by Bernoulli's Equation
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Verified Pressure Coefficient
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Verified Static Pressure in Incompressible Flow
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3 More Bernoulli's Equation and Pressure Concepts Calculators
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Blast Wave Part Theory (6)
Created Pressure Coefficient Combined with Blast Wave for Shuttle
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Created Pressure Coefficient Combined with Blast Wave for Shuttle at Angle of Attack
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Created Pressure Coefficient for Blast Wave Theory
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Created Pressure Coefficient for Blast Wave Theory at Very High Values of Mach
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Created Pressure Coefficient for Blunt-Nosed Cylinder
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Created Pressure Coefficient for Blunt-Nosed Plate
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Body Centered Cubic (3)
Created Atomic Radius in BCC
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Created Lattice Constant of BCC
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Created Total Volume of Atoms in BCC
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Body Lying on Rough Horizontal Plane (1)
Verified Tension in String given Coefficient of Friction of Horizontal Plane
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1 More Body Lying on Rough Horizontal Plane Calculators
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Body Lying on Rough Inclined Plane (5)
Verified Acceleration of System with Bodies One Hanging Free, Other Lying on Rough Inclined Plane
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Verified Coefficient of Friction given Tension
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Verified Inclination of Plane for given Frictional Force
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Verified Mass of Body B given Frictional Force
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Verified Tension in String given Coefficient of Friction of Inclined Plane
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2 More Body Lying on Rough Inclined Plane Calculators
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Body Lying on Rough Inclined Plane (1)
Verified Frictional Force on Body A
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5 More Body Lying on Rough Inclined Plane Calculators
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Body Lying on Smooth Inclined Plane (3)
Verified Acceleration of System with Bodies One Hanging Free and Other Lying on Smooth Inclined Plane
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Verified Angle of Inclination given Acceleration
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Verified Angle of Inclination given Tension
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1 More Body Lying on Smooth Inclined Plane Calculators
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Body Lying on Smooth Inclined Plane (2)
Verified Acceleration of System with Bodies Connected by String and Lying on Smooth Inclined Planes
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Verified Tension in String if Both Bodies are Lying on Smooth Inclined Planes
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2 More Body Lying on Smooth Inclined Plane Calculators
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Boundary Layer Flow (10)
Verified Area of Surface for Average Drag Coefficient
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Verified Distance from Leading Edge
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Verified Distance from Leading Edge for Blasius's Solution
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Verified Length of Plate for Reynold Number
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Verified Reynold Number at End of Plate
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Verified Reynold Number for Drag Coefficient in Blasius's Solution
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Verified Shear Stress at Boundary for Turbulent Boundary Layer over Flat Plate
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Verified Thickness of Boundary Layer
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Verified Thickness of Boundary Layer for Blasius's Solution
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Verified Velocity of Fluid for Reynold Number
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11 More Boundary Layer Flow Calculators
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Buoyancy (3)
Verified Angle of heel for metacentric height in experimental method
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Verified Meta-centric height in experimental method
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Verified Movable weight for metacentric height in experimental method
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8 More Buoyancy Calculators
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Climbing Flight (3)
Verified Rate of Climb
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Verified Rate of Climb for given excess power
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Verified Weight of Aircraft for given Excess Power
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13 More Climbing Flight Calculators
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Compressible Flow Parameters (1)
Verified Pressure Ratio for Maximum Flow Rate through Nozzle
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9 More Compressible Flow Parameters Calculators
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Compression Waves (3)
Created Density before Shock Formation for Compression Wave
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Created New Pressure after Shock Formation for Compression Wave
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Created Temperature Ratio for Unsteady Compression Waves
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Computational Fluid Dynamic Solutions (4)
Created Emissivity
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Created Freestream Density
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Created Freestream Velocity
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Created Reference Viscosity
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7 More Computational Fluid Dynamic Solutions Calculators
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Conduction (1)
Created Fourier's Law of Heat Conduction
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5 More Conduction Calculators
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Conduction in Cylinder (3)
Verified Total Thermal Resistance of 2 Cylindrical Resistances Connected in Series
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Verified Total Thermal Resistance of 3 Cylindrical Resistances Connected in Series
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Verified Total Thermal Resistance of Cylindrical Wall with Convection on Both Sides
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13 More Conduction in Cylinder Calculators
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Conduction in Sphere (2)
Verified Heat Flow Rate through Spherical Wall
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Verified Thermal Resistance of Spherical Wall
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9 More Conduction in Sphere Calculators
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Cutting Force (1)
Created Cutting Force given Thrust Force and Normal Rake Angle
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5 More Cutting Force Calculators
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Cylinder Properties (1)
Verified Radius of Cylinder for Single Stagnation Point
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6 More Cylinder Properties Calculators
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Cylindrical Blast Wave (8)
Created Boltzmann Constant for Cylindrical Blast Wave
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Created Modified Energy for Cylindrical Blast Wave
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Created Modified Pressure Equation for Cylindrical Blast Wave
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Created Modified Radial Coordinate Equation for Cylindrical Blast Wave
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Created Pressure for Cylindrical Blast Wave
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Created Pressure Ratio for Blunt Slab Blast Wave
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Created Radial Coordinate of Cylindrical Blast Wave
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Created Simplified Pressure Ratio for Blunt Cylinder Blast Wave
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Dimensionless Quantities (4)
Created Nusselt's Number with Reynolds Number, Stanton Number and Prandtl Number
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Created Prandtl Number with Reynolds Number, Nusselt's Number, and Stanton Number
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Created Reynolds Number for given Nusselt's Number, Stanton Number and Prandtl Number
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Created Stanton Number with Reynolds Number, Nusselt's Number, Stanton Number and Prandtl Number
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Dimensions and Geometry (7)
Verified Diameter of Pipe for Difference in Pressure in Viscous Flow
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Verified Diameter of Pipe for Head Loss due to Friction in Viscous Flow
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Verified Diameter of Pipe for Loss of Pressure Head in Viscous Flow
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Verified Diameter of Pipe from Maximum Velocity and Velocity at Any Radius
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Verified Length of Pipe for Difference of Pressure in Viscous Flow
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Verified Length of Pipe for Head Loss due to Friction in Viscous Flow
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Verified Length of Pipe for Loss of Pressure Head in Viscous Flow
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12 More Dimensions and Geometry Calculators
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Discharge (2)
Verified Coefficient of Discharge for Time Required to Empty Reservoir
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Verified Time Required to Empty Reservoir
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15 More Discharge Calculators
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Doublet Flow (1)
Verified Velocity Potential for 2-D Doublet Flow
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1 More Doublet Flow Calculators
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Downstream Shock Waves (3)
Verified Enthalpy behind Normal Shock from Normal Shock Energy Equation
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Verified Mach Number behind Shock
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Verified Velocity behind Normal Shock by Normal Shock Momentum Equation
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12 More Downstream Shock Waves Calculators
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Drag and Forces (4)
Verified Coefficient of drag for sphere in Oseen formula when Reynolds number is between 0.2 and 5
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Verified Coefficient of drag for sphere in stoke's law when Reynolds number is less than 0.2
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Verified Drag Force for body moving in Fluid of Certain Density
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Verified Total Drag force on Sphere
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7 More Drag and Forces Calculators
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Elements of Kinetic Theory (15)
Created Emissivity per Unit Mole
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Created Kinetic Energy per Mole
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Created Kinetic Energy per Mole using Molar Volume
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Created Kinetic Energy per Mole using Temperature of Gas
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Created Mean Free Path of Single-Species Gas
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Created Mean Free Path using Number Density
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Created Molar Volume using Kinetic Energy per Mole
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Created Number Density
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Created Pressure of Gas using Number Density
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Created Pressure using Kinetic Energy per Mole
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Created Pressure using Molar Volume
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Created Specific Gas Constant using Kinetic Energy per Mole
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Created Temperature of Gas using Emissivity per Unit Mole
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Created Temperature of Gas using Kinetic Energy per Mole
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Created Volume of Gas
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Expansion Waves (5)
Created Density before Shock Formation for Expansion Wave
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Created New Pressure after Shock Formation, Subtracted to Velocity for Expansion Wave
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Created Pressure Ratio for Unsteady Waves with Subtracted Induced Mass Motion for Expansion Waves
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Created Ratio of New and Old Temperature for Expansion Waves
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Created Temperature Ratio for Unsteady Expansion Wave
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Face Centered Crystal (3)
Created Atomic Radius in FCC
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Created Lattice Constant of FCC
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Created Volume of Atoms in FCC
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Flow Analysis (4)
Verified Loss of Head Due to Friction
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Verified Loss of Pressure Head for Viscous Flow through Circular Pipe
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Verified Viscosity of Fluid or Oil for Movement of Piston in Dash-Pot
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Verified Viscosity of Fluid or Oil in Rotating Cylinder Method
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9 More Flow Analysis Calculators
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Flow Head (1)
Verified Head of Liquid above Centre of Orifice
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5 More Flow Head Calculators
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Flow in Open Channels (12)
Verified Bazin's constant
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Verified Chezy's constant considering Bazin formula
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Verified Chezy's constant considering velocity
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Verified Critical depth considering flow in open channels
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Verified Critical depth considering minimum specific energy
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Verified Critical Depth using Critical Velocity
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Verified Critical velocity considering flow in open channels
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Verified Discharge per unit width considering flow in open channels
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Verified Hydraulic mean depth considering Bazin formula
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Verified Hydraulic mean depth using Chezy's formula
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Verified Minimum Specific Energy using Critical Depth
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Verified Velocity of Chezy's formula
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7 More Flow in Open Channels Calculators
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Flow over Airfoils (4)
Verified Boundary Layer Thickness for Turbulent Flow
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Verified Center of Pressure Location for Cambered Airfoil
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Verified Skin Friction Drag Coefficient for Flat Plate in Laminar Flow
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Verified Skin Friction Drag Coefficient for Flat Plate in Turbulent Flow
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4 More Flow over Airfoils Calculators
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Flow Rate (4)
Verified Coefficient of Discharge given Time of Emptying Hemispherical Tank
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Verified Discharge in Borda's Mouthpiece Running Free
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Verified Discharge in Borda's Mouthpiece Running Full
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Verified Discharge in Convergent-Divergent Mouthpiece
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7 More Flow Rate Calculators
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Flow Regime (6)
Verified Coefficient of contraction for sudden contraction
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Verified Retarding force for gradual closure of valves
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Verified Time taken by pressure wave to travel
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Verified Velocity at Outlet for Head Loss at Exit of Pipe
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Verified Velocity of Fluid for Head Loss due to Obstruction in Pipe
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Verified Velocity of liquid at vena-contracta
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11 More Flow Regime Calculators
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Fluid Flow and Resistance (5)
Verified Angular Speed of Outer Cylinder in Rotating Cylinder Method
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Verified Maximum Velocity at any Radius using Velocity
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Verified Total Torque Measured by Strain in Rotating Cylinder Method
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Verified Velocity at Any Radius given Radius of Pipe, and Maximum Velocity
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Verified Velocity of Piston or Body for Movement of Piston in Dash-Pot
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16 More Fluid Flow and Resistance Calculators
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Fluid Parameters and Characteristics (2)
Verified Freestream Velocity for single Stagnation Point
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Verified Tangential velocity for single stagnation point
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7 More Fluid Parameters and Characteristics Calculators
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Forces and Friction (3)
Created Coefficient of friction for given friction angle
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Created Coefficient of friction for given thrust force, cutting force and normal rake angle
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Created Coefficient of Friction given Forces Normal and along Tool Rake Face
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3 More Forces and Friction Calculators
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Fundamental of Heat Transfer (2)
Verified Thermal Conductance for given Thermal Resistance
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Verified Total Thermal Resistance for Conduction through Two Resistances in Parallel
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8 More Fundamental of Heat Transfer Calculators
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Geometric DImension (1)
Verified Length of Crest of Weir or Notch
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9 More Geometric DImension Calculators
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Geometric Dimensions (7)
Verified Area at vena contracta for discharge and constant head
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Verified Area of Mouthpiece in Borda's Mouthpiece Running Free
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Verified Area of Mouthpiece in Borda's Mouthpiece Running Full
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Verified Area of Orifice given Time of Emptying Hemispherical Tank
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Verified Coefficient of Contraction given Area of Orifice
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Verified Horizontal distance for coefficient of velocity and vertical distance
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Verified Vertical distance for coefficient of velocity and horizontal distance
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1 More Geometric Dimensions Calculators
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Geometric Property (1)
Verified Maximum Area of Obstruction in Pipe
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6 More Geometric Property Calculators
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Geometry and Dimensions (3)
Created Area of shear plane for given shear angle, width of cut and uncut chip thickness
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Created Side cutting edge angle for given width of cut
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Created Width of cut for given side cutting edge angle
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5 More Geometry and Dimensions Calculators
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Gliding Flight (2)
Verified Lift Force for given Glide Angle
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Verified Lift-to-drag ratio for given glide angle
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4 More Gliding Flight Calculators
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Governing Equations and Sound Wave (3)
Verified Mayer's Formula
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Verified Ratio of Stagnation and Static Density
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Verified Ratio of Stagnation and Static Temperature
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15 More Governing Equations and Sound Wave Calculators
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High Load Factor Maneuver (2)
Verified Lift Coefficient for given wing loading and turn radius
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Verified Wing Loading for given Turn Radius
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15 More High Load Factor Maneuver Calculators
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Hypersonic Flight Paths Velocity of Altitude Map (9)
Created Blunt-Nosed Radial Coordinate Flat Plate (First Approximation)
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Created Forces Acting on Body along Flight Path
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Created Forces Acting Perpendicular to Body on Flight Path
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Created Pressure Ratio of Blunt-Nosed Cylinder (First Approximation)
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Created Radial Coordinate of Blunt-Nosed Cylinder (First Approximation)
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Created Radius for Cylinder-Wedge Body Shape
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Created Radius for Sphere-Cone Body Shape
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Created Radius of Curvature for Cylinder Wedge Body Shape
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Created Radius of Curvature for Sphere Cone Body Shape
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Hypersonic Flow and Disturbances (17)
Created Change in Velocity for Hypersonic Flow in X Direction
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Created Coefficient of Pressure with Slenderness Ratio
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Created Coefficient of Pressure with Slenderness Ratio and Similarity Constant
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Created Constant G used for Finding Location of Perturbed Shock
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Created Density Ratio with Similarity Constant having Slenderness Ratio
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Created Distance from Tip of Leading Edge to Base
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Created Doty and Rasmussen- Normal Force Coefficient
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Created Inverse of Density for Hypersonic Flow
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Created Inverse of Density for Hypersonic Flow using Mach Number
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Created Non Dimensional Change in Hypersonic Disturbance Velocity in x Direction
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Created Non Dimensional Change in Hypersonic Disturbance Velocity in y Direction
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Created Non Dimensional Pressure Equation with Slenderness Ratio
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Created Non Dimensional Velocity Disturbance in y Direction in Hypersonic Flow
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Created Non Dimensionalised Time
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Created Rasmussen Closed Form Expression for Shock Wave Angle
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Created Similarity Constant Equation using Wave Angle
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Created Similarity Constant Equation with Slenderness Ratio
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Hypersonic Flow Parameters (19)
Created Axial Force Coefficient
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Created Coefficient of Drag
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Created Coefficient of Pressure with Similarity Parameters
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Created Deflection Angle
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Created Drag Force
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Created Dynamic Pressure
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Created Dynamic Pressure given Coefficient of Lift
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Created Hypersonic Similarity Parameter
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Created Lift Coefficient
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Created Lift Force
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Created Mach Number with Fluids
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Created Mach Ratio at High Mach Number
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Created Moment Coefficient
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Created Newtonian Sine Squared Law for Pressure Coefficient
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Created Normal Force Coefficient
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Created Pressure Ratio for High Mach Number
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Created Pressure Ratio having High Mach Number with Similarity Constant
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Created Shear-Stress Distribution
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Created Supersonic Expression for Pressure Coefficient on Surface with Local Deflection Angle
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1 More Hypersonic Flow Parameters Calculators
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Hypersonic Flow Parameters (7)
Created Dynamic Viscosity around Wall
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Created Local Shear Stress at Wall
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Created Local Skin-Friction Coefficient
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Created Skin Friction Coefficient for Incompressible Flow
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Created Static Density Equation using Skin Friction Coefficient
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Created Static Velocity Equation using Skin Friction Coefficient
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Created Static Viscosity Relation using Temperature of Wall
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Hypersonic Transition (16)
Created Boundary-Layer Momentum Thickness using Reynolds Number at Transition Point
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Created Eddy Viscosity Calculation
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Created Local Mach Number using Reynolds Number Equation at Transition Region
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Created Location of Transition Point
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Created Prandtl Number of Transition Flow
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Created Reynolds Number Equation using Boundary-Layer Momentum Thickness
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Created Reynolds Number Equation using Local Mach Number
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Created Specific Heat at Constant Pressure for Transient Flow
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Created Static Density at Transition Point
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Created Static Density Equation using Boundary-Layer Momentum Thickness
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Created Static Velocity at Transition Point
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Created Static Velocity using Boundary-Layer Momentum Thickness
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Created Static Viscosity at Transition Point
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Created Static Viscosity Equation using Boundary-Layer Momentum Thickness
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Created Thermal Conductivity of Transition Flow
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Created Transition Reynolds Number
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Incompressible Flow Characteristics (1)
Verified Radius of Rankine circle
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22 More Incompressible Flow Characteristics Calculators
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Jet Airplane (5)
Verified Endurance for given Lift-to-Drag Ratio of Jet Airplane
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Verified Lift-to-Drag Ratio for given Endurance of Jet Airplane
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Verified Range of Jet Airplane
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Verified Thrust-Specific Fuel Consumption for given Endurance and Lift-to-Drag Ratio of Jet Airplane
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Verified Thrust-Specific Fuel Consumption for given Range of Jet Airplane
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12 More Jet Airplane Calculators
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Kinematics of Flow (7)
Verified Actual Discharge in Venturimeter
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Verified Difference in Pressure Head for heavier Liquid in Manometer
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Verified Difference in pressure head for light liquid in manometer
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Verified Height or depth of paraboloid for volume of air
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Verified Total Pressure Force at Bottom of Cylinder
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Verified Total pressure force on top of cylinder
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Verified Velocity at any point for coefficient of pitot-tube
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10 More Kinematics of Flow Calculators
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Kutta Joukowski Lift Theorem (1)
Verified Lift Per Unit Span by Kutta-Joukowski Theorem
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3 More Kutta Joukowski Lift Theorem Calculators
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Laminar Boundary Layer at Stagnation point on Blunt body (7)
Created Newtonian Dynamic Pressure
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Created Newtonian Pressure Distribution over Surface using Cosine Angle
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Created Nusselt Number at Stagnation Point
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Created Nusselt Number for Stagnation Point on Blunt Body
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Created Reynolds Analogy Factor in Finite Deference Method
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Created Reynolds Analogy for Stanton Number in Finite Difference Method
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Created Stagnation Pressure
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Landing (1)
Verified Landing ground roll distance
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4 More Landing Calculators
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Lift and Circulation (1)
Verified Circulation for Single Stagnation Point
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15 More Lift and Circulation Calculators
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Lift and Drag Requirements (2)
Verified Coefficient of Drag for given Thrust and Weight
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Verified Lift-Induced Drag Coefficient given required Thrust
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17 More Lift and Drag Requirements Calculators
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Lifting Flow over Cylinder (1)
Verified Tangential Velocity for Lifting Flow over Circular Cylinder
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9 More Lifting Flow over Cylinder Calculators
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Local Heat Transfer for Hypersonic Flow (9)
Created Adiabatic Wall Enthalpy using Stanton Number
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Created Enthalpy of Wall using Stanton Number
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Created Local Heat Transfer Rate Calculation using Stanton Number
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Created Local Heat Transfer Rate using Nusselt's Number
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Created Nusselt Number for Hypersonic Vehicle
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Created Stanton Number for Hypersonic Vehicle
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Created Static Density Equation using Stanton Number
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Created Static Velocity using Stanton Number
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Created Thermal Conductivity at Edge of Boundary Layer Equation using Nusselt's Number
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Modern Design Oriented Code (2)
Created Convective Heat Transfer to Surface
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Created Radiative Heat Transfer to Surface Stemming from Thermal Radiation
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Multiphase Compressible Flow (5)
Verified Absolute Temperature for Velocity of Sound Wave in Isothermal Process
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Verified Absolute Temperature for Velocity of Sound Wave using Adiabatic Process
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Verified Density of Fluid considering Velocity at Outlet of Orifice
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Verified Velocity of Sound Wave using Adiabatic Process
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Verified Velocity of Sound Wave using Isothermal Process
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2 More Multiphase Compressible Flow Calculators
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Newtonian Flow (14)
Created Coefficient of Drag Equation with Angle of Attack
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Created Coefficient of Drag Equation with Coefficient of Normal Force
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Created Coefficient of Lift Equation with Angle of Attack
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Created Coefficient of Lift Equation with Coefficient of Normal Force
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Created Drag Force with Angle of Attack
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Created Exact Normal Shock Wave Maximum Coefficient of Pressure
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Created Force Exerted on Surface given Static Pressure
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Created Lift Force with Angle of Attack
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Created Mass Flux Incident on Surface Area
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Created Maximum Pressure Coefficient
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Created Modified Newtonian Law
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Created Pressure Coefficient for Slender 2D Bodies
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Created Pressure Coefficient for Slender Bodies of Revolution
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Created Time Rate of Change of Momentum of Mass Flux
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Nonlifting Flow over Cylinder (2)
Verified Radial Velocity for Non-Lifting Flow over Circular Cylinder
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Verified Surface Pressure Coefficient for Non-Lifting Flow over Circular Cylinder
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8 More Nonlifting Flow over Cylinder Calculators
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Normal Shock Relations (4)
Verified Characteristic Mach Number
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Verified Critical Speed of Sound from Prandtl Relation
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Verified Downstream Velocity using Prandtl Relation
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Verified Upstream Velocity using Prandtl Relation
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3 More Normal Shock Relations Calculators
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Oblique Shock (1)
Verified Component of Upstream Mach Normal to Oblique Shock
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9 More Oblique Shock Calculators
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Oblique Shock Relation (15)
Created Coefficient of Pressure Derived from Oblique Shock Theory
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Created Density Ratio when Mach Becomes Infinite
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Verified Dynamic Pressure for given Specific Heat Ratio and Mach Number
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Created Exact Density Ratio
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Created Exact Pressure Ratio
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Created Non-Dimensional Pressure Coefficient
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Created Parallel Upstream Flow Components after Shock as Mach Tends to Infinite
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Created Perpendicular Upstream Flow Components behind Shock Wave
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Created Pressure Coefficient behind Oblique Shock Wave
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Created Pressure Coefficient behind Oblique Shock Wave for Infinite Mach Number
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Created Pressure Ratio when Mach becomes Infinite
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Created Temperature Ratio when Mach Becomes Infinite
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Created Temperature Ratios
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Created Velocity of Sound using Dynamic Pressure and Density
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Created Wave Angle for Small Deflection Angle
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Parameters (1)
Created Atomic Packing Factor
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4 More Parameters Calculators
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Planar and Blunt Slab Blast Wave (8)
Created Blunt-Nosed Flat Plate Pressure Ratio (First Approximation)
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Created Coefficient of Drag Equation using Energy Released from Blast Wave
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Created Creation Pressure for Planar Blast Wave
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Created Energy for Blast Wave
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Created Pressure Ratio for Blunt Cylinder Blast Wave
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Created Radial Coordinate for Planar Blast Wave
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Created Radial Coordinate of Blunt Slab Blast Wave
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Created Time Required for Blast Wave
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Power Transmission (3)
Verified Efficiency of power transmission in flow through pipes
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Verified Power Lost ue to Sudden Enlargement
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Verified Power transmission through pipes
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2 More Power Transmission Calculators
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Preliminary Aerodynamics (1)
Verified Velocity at Altitude
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16 More Preliminary Aerodynamics Calculators
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Pressure and Flow Head (7)
Verified Difference in liquid level in three compound pipes with same friction coefficient
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Verified Head available at Base of Nozzle
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Verified Head Loss due to Friction for Efficiency of Power Transmission
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Verified Loss of head at exit of pipe
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Verified Loss of Head due to Obstruction in Pipe
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Verified Total head at inlet of pipe for head available at base of nozzle
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Verified Total head available at inlet of pipe for efficiency of power transmission
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7 More Pressure and Flow Head Calculators
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Propeller Driven Airplane (2)
Verified Lift-to-Drag ratio for given Range of Propeller-Driven Airplane
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Verified Shaft Brake Power for Reciprocating Engine-Propeller Combination
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20 More Propeller Driven Airplane Calculators
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Reference Temperature Method (15)
Created Chord Length for Flat Plate Case
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Created Local Reynolds Number
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Created Local Turbulent Skin-Friction Coefficient for Incompressible Flow
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Created Mach Number at Reference Temperature
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Created Overall Skin-Friction Drag Coefficient
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Created Overall Skin-Friction Drag Coefficient for Incompressible Flow
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Created Reference Temperature Equation
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Created Reynolds Number for Chord Length
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Created Reynolds Number for Chord Length using Overall Skin-Friction Drag Coefficient
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Created Stanton Number Obtained from Classical Theory
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Created Static Density of Plate using Chord Length for Flat Plate Case
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Created Static Velocity of Plate using Chord Length for Flat Plate Case
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Created Static Viscosity of Plate using Chord Length for Flat Plate Case
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Created Turbulent Flat-Plate Skin-Friction Coefficient
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Created Wall Temperature using Reference Temperature
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Resultants and Stress (1)
Created Force acting Normal to Rake Face given Cutting Force and Thrust Force
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5 More Resultants and Stress Calculators
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Shock Dynamics and Aerodynamic Shape (10)
Created Detachment Distance of Cylinder Wedge Body Shape
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Created Detachment Distance of Sphere Cone Body Shape
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Created Grid Point Calculation for Shock Waves
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Created Local Shock Velocity Equation
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Created Mach Wave behind Shock
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Created Mach Wave behind Shock with Mach Infinity
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Created Nose Radius of Cylinder-Wedge
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Created Nose Radius of Sphere Cone
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Created Pressure Ratio for Unsteady Waves
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Created Ratio of New and Old Temperature
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Simple Cubic Cell (3)
Created Atomic Radius in SCC
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Created Lattice Constant of SCC
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Created Total Volume of Atoms in SCC
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Single Plane Wall (1)
Verified Total Thermal Resistance of Plane Wall with Convection on Both Sides
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7 More Single Plane Wall Calculators
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Source Flow (2)
Verified Stream Function for Flow over Rankine Oval
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Verified Velocity Potential for 2-D Source Flow
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5 More Source Flow Calculators
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Space Marching Finite Difference Method Additional Solutions of the Euler Equations (11)
Created Coefficient of Pressure Equation using Specific Heat Ratio
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Created Curvilinear Grid Location Equation
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Created Density Equation using Enthalpy and Pressure
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Created Enthalpy Equation using Coefficient of Pressure for Calorically Perfect Gas
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Created Enthalpy Equation using Pressure and Density
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Created Enthalpy Equation using Specific Heat Ratio
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Created Free Stream Enthalpy
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Created Local Shock-Layer Thickness
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Created Pressure Equation using Enthalpy and Density
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Created Total Enthalpy Equation using Specific Heat Ratio and Velocities
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Created Total Specific Enthalpy
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Stagnation Properties (2)
Verified Stagnation Temperature considering Compressible Fluid Flow
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Verified Temperature of Fluid for Stagnation Temperature considering Compressible Fluid Flow
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6 More Stagnation Properties Calculators
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Static Parameters for Hypersonic Flow (6)
Created Static Density of Fluid over Flat Plate
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Created Static Temperature of Fluid over Flat Plate
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Created Static Temperature of Plate using Wall Viscosity
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Created Static Temperature over Flat Plate under Viscous, Very High Mach Flow
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Created Static Temperature over Flat Plate using Static Mach Number
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Created Static Viscosity using Wall Temperature and Static Temperature
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Stick Forces and Hinge Moments (6)
Verified Control stick length for given gearing ratio
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Verified Elevator Chord Length given Stick Force
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Verified Elevator Deflection Angle given Gearing Ratio
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Verified Elevator Stick Force given Gearing Ratio
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Verified Flight Velocity given Elevator Hinge Moment Coefficient
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Verified Hinge Moment Coefficient given Stick Force
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17 More Stick Forces and Hinge Moments Calculators
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Supersonic Aerothermodynamics (8)
Created Large Mach Number over Flat Plate using Static Temperature and Wall Temperature
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Created Mach Number over Flat Plate using Static Temperature and Wall Temperature
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Created Pressure Ratio for Cold-Wall Case Strong Interaction
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Created Pressure Ratio for Cold-Wall Case Weak Interaction
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Created Total Temperature over Flat Plate under Viscous Mach Flow
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Created Total Temperature over Flat Plate under Viscous Very High Mach Flow
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Created Viscosity of Wall using Wall Temperature and Static Temperature
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Created Wall Density of Fluid over Flat Plate
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Tail Contribution (5)
Verified Horizontal Tail Volume Ratio for given Pitching Moment Coefficient
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Verified Mean Aerodynamic Chord for given Tail Pitching Moment Coefficient
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Verified Tail Efficiency for given Tail Volume Ratio
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Verified Tail Lift Coefficient for given Tail Volume Ratio
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Verified Tail Pitching Moment Coefficient for given Tail Volume Ratio
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14 More Tail Contribution Calculators
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Take Off (1)
Verified Liftoff velocity for given stall velocity
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14 More Take Off Calculators
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Thermodynamics and Governing Equations (1)
Verified Mach Angle
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18 More Thermodynamics and Governing Equations Calculators
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Thrust and Power Requirements (5)
Verified Minimum Thrust required for given weight
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Verified Power required for given aerodynamic coefficients
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Verified Thrust of Aircraft required for given required Power
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Verified Thrust-to-weight ratio
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Verified Weight of aircraft for given required power
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14 More Thrust and Power Requirements Calculators
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Thrust Force (2)
Created Thrust force for given frictional force along tool rake face, cutting force and normal rake angle
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Created Thrust Force given Cutting Force and Normal Rake Angle
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2 More Thrust Force Calculators
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Turbulent Flow (2)
Verified Shear Stress Developed for Turbulent Flow in Pipes
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Verified Shear Velocity for Turbulent Flow in Pipes
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16 More Turbulent Flow Calculators
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Turning Flight (1)
Verified Weight of aircraft during level turn
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12 More Turning Flight Calculators
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Uniform Flow (2)
Verified Stream Function for Uniform Incompressible Flow in Polar Coordinates
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Verified Velocity Potential for Uniform Incompressible Flow in Polar Coordinates
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2 More Uniform Flow Calculators
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Upstream Shock Waves (2)
Verified Enthalpy ahead of Normal Shock from Normal Shock Energy Equation
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Verified Velocity ahead of Normal Shock by Normal Shock Momentum Equation
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5 More Upstream Shock Waves Calculators
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Velocity and Time (2)
Verified Coefficient of velocity
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Verified Time of Emptying Hemispherical Tank
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6 More Velocity and Time Calculators
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Vertical Tail Contribution (1)
Verified Vertical Tail Efficiency
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23 More Vertical Tail Contribution Calculators
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Viscous Flow (15)
Created Adiabatic Wall Enthalpy for Flat Plate
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Created Adiabatic Wall Enthalpy using Recovery Factor
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Created Aerodynamic Heating Equation for Stanton number
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Created Coefficient of Friction using Stanton Number for Flat Plate Case
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Created Drag per Unit Span
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Created Prandtl Number for Flat Plate with Viscous Flow
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Created Recovery Factor Calculation using Prandtl Number
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Created Recovery Factor for Flat Plate with Viscous Flow
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Created Recovery Factor using Temperature
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Created Skin-Friction Drag Coefficient
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Created Skin-Friction Drag for Flat Plate in Viscous Flow
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Created Stanton Number with Coefficient of Friction
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Created Static Density Equation using Aerodynamic Equation
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Created Static Velocity Equation using Aerodynamic Heating Equation
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Created Total Enthalpy in Inviscid Flow Outside Boundary Layer
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Vortex Flow (1)
Verified Tangential Velocity for 2-D Vortex Flow
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2 More Vortex Flow Calculators
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Wall Temperature (4)
Created Wall Temperature of Fluid over Flat Plate
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Created Wall Temperature of Plate using Wall Viscosity
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Created Wall Temperature over Flat Plate under Viscous, Very High Mach Flow
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Created Wall Temperature over Flat Plate using Static Mach Number
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Wing Tail Contribution (1)
Verified Angle of incidence of wing
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14 More Wing Tail Contribution Calculators
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Wing Tail Interaction (2)
Verified Dynamic Pressure at Vertical Tail for given Vertical Tail Efficiency
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Verified Dynamic Pressure at Wing for given Vertical Tail Efficiency
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10 More Wing Tail Interaction Calculators
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Percentage calculator Fraction calculator LCM HCF Calculator
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