Calculators Created by Vinay Mishra

Verified Heat Flow Rate through Composite Wall of 2 Layers in Series

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Verified Interface Temperature of Composite Wall of 2 Layers given Inner Surface Temperature

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Verified Length of 2nd Layer of Composite Wall in Conduction through Walls

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Verified Outer Surface Temperature of Composite Wall of 2 Layers for Conduction

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4 More 2 Layers Calculators

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Verified Heat Flow Rate through Composite Wall of 3 Layers in Series

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Verified Outer Surface Temperature of Composite Wall of 3 Layers for Conduction

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4 More 3 Layers Calculators

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Verified Height Difference of Manometric Fluid for given Pressure Difference

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Verified Surface Pressure on Body using Pressure Coefficient

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Verified Wind Tunnel Pressure Difference with Test Speed

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7 More Aerodynamic Measurements and Wind Tunnel Testing Calculators

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Created Sideslip Angle for Aircraft

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Created Sideslip Angle for given Moment Produced by Vertical Tail

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Created SideSlip Angle for given Yawing Moment Coefficient

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Created Sideslip Angle given Yawing Moment Coefficient and Tail Efficiency

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Created Sidewash angle

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Created Sidewash Angle for given Moment Produced by Vertical Tail

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Created Sidewash Angle for given Yawing Moment Coefficient

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Created Sidewash Angle given Yawing Moment Coefficient using Wingspan

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Created Yawing Moment Coefficient for given Vertical Tail Lift Curve Slope

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Created Yawing Moment Coefficient for given Vertical Tail Volume Ratio

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Created Yawing Moment Coefficient using Wingspan

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Created Aerodynamic Axial Force

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Created Aerodynamic Normal Force

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Created Aerodynamic Side Force

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Created Angle of attack

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Created Normal Force Coefficient with Aerodynamic Normal Force

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Created Pitching moment

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Created Pitching moment coefficient

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Created Rolling Moment

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Created Rolling moment coefficient

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Created Side force coefficient

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Created Sideslip angle

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Created Velocity along Pitch Axis for Small Sideslip Angle

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Created Velocity along Roll Axis for Small Angle of Attack

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Created Velocity along Roll Axis for Small Sideslip Angle

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Created Velocity along Yaw Axis for Small Angle of Attack

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Created Yawing Moment

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Created Yawing moment coefficient

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1 More Aircraft Dynamics Nomenclature Calculators

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Verified Adiabatic Wall Enthalpy over Flat Plate using Stanton Number

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Verified Freestream Density over Flat Plate using Stanton Number

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Verified Freestream Velocity over Flat Plate using Stanton Number

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Verified Wall Enthalpy over Flat Plate using Stanton Number

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11 More Approximate Results Applied to Hypersonic Vehicles Calculators

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Created Absolute altitude

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Created Geometric altitude

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Created Geometric altitude for given geopotential altitude

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Created Geopotential altitude

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Created Lapse rate

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9 More Atmosphere and Gas Properties Calculators

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Verified Pressure at Downstream Point by Bernoulli's Equation

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Verified Velocity at Point on Airfoil for given Pressure Coefficient and Free-Stream Velocity

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4 More Bernoulli's Equation and Pressure Concepts Calculators

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Verified Pressure Coefficient for Blast Wave Theory at Very High Values of Mach

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Verified Pressure Coefficient for Blunt-Nosed Plate

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4 More Blast Wave Part Theory Calculators

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Created Acceleration of System with Bodies One Hanging Free and Other Lying on Rough Horizontal Plane

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Created Tension in String given Coefficient of Friction of Horizontal Plane

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Created Acceleration of System with Bodies One Hanging Free, Other Lying on Rough Inclined Plane

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Created Coefficient of Friction given Frictional Force

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Created Coefficient of Friction given Tension

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Created Frictional Force

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Created Inclination of Plane for given Frictional Force

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Created Mass of Body B given Frictional Force

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Created Tension in String given Coefficient of Friction of Inclined Plane

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Created Acceleration of System given Mass of Body A

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Created Acceleration of System given Mass of Body B

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Created Frictional Force on Body A

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Created Frictional Force on Body B

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Created Tension in String given Mass of Body A

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Created Tension in String given Mass of Body B

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Created Acceleration in System

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Created Tension in String if only One Body is Freely Suspended

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Created Acceleration of System with Bodies One Hanging Free and Other Lying on Smooth Inclined Plane

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Created Angle of Inclination given Acceleration

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Created Angle of Inclination given Tension

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Created Tension in String when One Body is Lying on Smooth Inclined Plane

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Created Acceleration of System with Bodies Connected by String and Lying on Smooth Inclined Planes

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Created Angle of Inclination of Plane with Body A

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Created Angle of Inclination of Plane with Body B

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Created Tension in String if Both Bodies are Lying on Smooth Inclined Planes

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Created Acceleration of Bodies

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Created Mass of Body B of Smaller Mass

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Created Tension in String if Both Bodies are Freely Hanging

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Verified Average Coefficient of Drag for Drag Force

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Verified Drag Force for Average Drag Coefficient

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Verified Freestream Velocity for Local Drag Coefficient

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Verified Local Drag Coefficient for Shear Stress

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Verified Shear Stress for Local Drag Coefficient

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16 More Boundary Layer Flow Calculators

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Verified Centre of Buoyancy

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Verified Meta-centric height for time period of oscillation and radius of gyration

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Verified Radius of gyration for metacentric height and time period of oscillation

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Verified Volume of fluid displaced

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7 More Buoyancy Calculators

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Created Centrifugal Force in Accelerated Flight

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Created Drag in Accelerated Flight

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Created Excess power

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Created Excess power for given rate of climb

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Created Flight path angle at given rate of climb

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Created Lift in Accelerated Flight

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Created Rate of Climb

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Created Rate of Climb for given excess power

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Created Thrust available for given excess power

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Created Thrust in Accelerated Flight

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Created Total Drag for given Excess Power

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Created Velocity in Accelerated Flight

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Created Velocity of aircraft at given rate of climb

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Created Velocity of Aircraft for given Excess Power

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Created Weight of Aircraft for given Excess Power

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1 More Climbing Flight Calculators

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Verified Bulk Modulus for Velocity of Sound Wave

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Verified Velocity of Sound Wave given Bulk Modulus

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8 More Compressible Flow Parameters Calculators

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Verified Heat Flow Rate through Cylindrical Composite Wall of 2 Layers

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Verified Heat Flow Rate through Cylindrical Composite Wall of 3 Layers

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Verified Heat Flow Rate through Cylindrical Wall

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Verified Inner Surface Temperature of Cylindrical Wall in Conduction

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Verified Outer Surface Temperature of Cylindrical Composite Wall of 2 Layers

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Verified Outer Surface Temperature of Cylindrical Wall given Heat Flow Rate

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Verified Thermal Conductivity of Cylindrical Wall given Temperature Difference

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Verified Thermal Resistance for Radial Heat Conduction in Cylinders

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8 More Conduction in Cylinder Calculators

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Verified Circulation for Lift Force on Cylinder

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Verified Length of Cylinder for Lift Force on Cylinder

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5 More Cylinder Properties Calculators

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Verified Modified Energy for Cylindrical Blast Wave

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7 More Cylindrical Blast Wave Calculators

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Verified Stanton Number with Reynolds Number, Nusselt's Number, Stanton Number and Prandtl Number

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3 More Dimensionless Quantities Calculators

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Verified Diameter of Sphere in Falling Sphere Resistance Method

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18 More Dimensions and Geometry Calculators

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Verified Discharge over Broad-Crested Weir

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Verified Discharge over Rectangle Notch or Weir

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Verified Discharge over Rectangle Weir for Bazin's formula with Velocity of Approach

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Verified Discharge over Rectangle Weir with Two End Contractions

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Verified Head of Liquid at Crest

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12 More Discharge Calculators

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Created Characteristic Mach Number behind Shock

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Verified Density behind Normal Shock using Normal Shock Momentum Equation

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Created Mach Number behind Shock

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Verified Stagnation Pressure behind Normal Shock by Rayleigh Pitot Tube formula

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Verified Static Pressure behind Normal Shock using Normal Shock Momentum Equation

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Created Velocity behind Normal Shock

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Verified Velocity behind Normal Shock from Normal Shock Energy Equation

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8 More Downstream Shock Waves Calculators

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Verified Prandtl Meyer Function

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Verified Prandtl Meyer Function at Upstream Mach Number

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Verified Pressure behind Expansion Fan

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Verified Rearward Mach Angle of Expansion Fan

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Verified Temperature behind Expansion Fan

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5 More Expansion Waves Calculators

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Verified Viscosity of Fluid or Oil in Falling Sphere Resistance Method

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12 More Flow Analysis Calculators

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Verified Head of liquid for head loss and coefficient of velocity

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Verified Loss of head due to fluid resistance

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4 More Flow Head Calculators

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Verified Lift Coefficient for Symmetrical Airfoil by Thin Airfoil Theory

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7 More Flow over Airfoils Calculators

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Verified Coefficient of Discharge given Time of Emptying Circular Horizontal Tank

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Verified Discharge through fully sub-merged orifice

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Verified Discharge through large rectangular orifice

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Verified Discharge through partially sub-merged orifice

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7 More Flow Rate Calculators

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Verified Time required to close Valve for Gradual Closure of Valves

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Verified Velocity at section 1-1 for sudden enlargement

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Verified Velocity at section 2-2 for sudden enlargement

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14 More Flow Regime Calculators

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Verified Buoyant Force in Falling Sphere Resistance Method

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Verified Density of Fluid in Falling Sphere Resistance Method

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Verified Drag Force in Falling Sphere Resistance Method

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Verified Velocity of Sphere in Falling Sphere Resistance Method

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17 More Fluid Flow and Resistance Calculators

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Verified Freestream Velocity for Lift Coefficient in Rotating Cylinder with Circulation

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Verified Freestream velocity for lift coefficient with tangential speed

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7 More Fluid Parameters and Characteristics Calculators

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Created Cutting Shear Force given Uncut Chip Thickness and Shear Angle

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3 More Force Normal to Shear Calculators

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Created Shear force acting on shear plane for given shear stress and area of shear plane

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5 More Forces and Friction Calculators

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Verified Thermal resistance for conduction through 2 resistances in parallel

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Verified Total Thermal Resistance for Conduction through Three Resistances in Series

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Verified Total Thermal Resistance for Conduction through Two Resistances in Series

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7 More Fundamental of Heat Transfer Calculators

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Verified Length of Section for Discharge over Rectangle Notch or Weir

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Verified Length of Weir Considering Bazin's formula with Velocity of Approach

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Verified Length of Weir for Discharge over Broad-Crested Weir

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7 More Geometric DImension Calculators

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Created Shear angle for given area of shear plane, width of cut and uncut chip thickness

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Created Uncut chip thickness for given width of cut, shear angle and area of shear plane

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Created Width of cut for given shear angle, uncut chip thickness and area of shear plane

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5 More Geometry and Dimensions Calculators

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Created Degree of Freedom

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Created Number of Components

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Created Number of Phases

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Created Total Number of Variables in System

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Created Drag for given Glide Angle

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Created Glide angle

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Created Glide angle for given lift-to-drag ratio

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Created Lift Force for given Glide Angle

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Created Lift-to-drag ratio for given glide angle

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1 More Gliding Flight Calculators

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Verified Critical Density

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Verified Critical Pressure

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Verified Critical Temperature

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Verified Isentropic Compressibility for given Density and Speed of Sound

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Created Mayer's Formula

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Created Ratio of Stagnation and Static Density

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Created Ratio of Stagnation and Static Pressure

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Created Ratio of Stagnation and Static Temperature

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10 More Governing Equations and Sound Wave Calculators

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Created Lift Coefficient for given Turn Radius

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Created Lift Coefficient for given Turn Rate

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Created Lift Coefficient for given wing loading and turn radius

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Created Load factor for given turn radius for high-performance fighter aircraft

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Created Load factor for given turn rate for high-performance fighter aircraft

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Created Radius of Turn for given Lift Coefficient

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Created Radius of Turn for given Wing Loading

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Created Turn radius for high load factor

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Created Turn Rate for given Lift Coefficient

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Created Turn Rate for given Wing Loading

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Created Turn Rate for High Load Factor

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Created Velocity for given pull-up maneuver rate

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Created Velocity given Turn Radius for High Load Factor

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Created Wing Loading for given Turn Radius

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Created Wing Loading for given Turn Rate

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2 More High Load Factor Maneuver Calculators

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Verified Axial Force Coefficient

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Verified Normal Force Coefficient

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18 More Hypersonic Flow Parameters Calculators

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Verified Local Skin-Friction Coefficient

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6 More Hypersonic Flow Parameters Calculators

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Verified Reynolds Number Equation using Boundary-Layer Momentum Thickness

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Verified Reynolds Number Equation using Local Mach Number

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Verified Thermal Conductivity of Transition Flow

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13 More Hypersonic Transition Calculators

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Verified Radial velocity at any radius

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Verified Radius at any point considering radial velocity

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Verified Stream function at point

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Verified Stream Function at Point in Combined Flow

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Verified Stream function in sink flow for angle

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Verified Strength of doublet for stream function

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Verified Strength of source for radial velocity and at any radius

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Verified Uniform flow velocity for stream function at point in combined flow

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15 More Incompressible Flow Characteristics Calculators

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Created Endurance for given Lift-to-Drag Ratio of Jet Airplane

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Created Endurance of Jet Airplane

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Created Lift-to-Drag Ratio for given Endurance of Jet Airplane

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Created Range of Jet Airplane

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Created Thrust-Specific Fuel Consumption for given Endurance and Lift-to-Drag Ratio of Jet Airplane

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Created Thrust-Specific Fuel Consumption for given Endurance of Jet Airplane

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Created Thrust-Specific Fuel Consumption for given Range of Jet Airplane

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10 More Jet Airplane Calculators

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Verified Circulation by Kutta-Joukowski Theorem

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3 More Kutta Joukowski Lift Theorem Calculators

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Verified Reynolds Analogy Factor in Finite Deference Method

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Verified Reynolds Analogy for Stanton Number in Finite Difference Method

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5 More Laminar Boundary Layer at Stagnation point on Blunt body Calculators

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Created Landing ground roll distance

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Created Stall velocity for given touchdown velocity

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Created Touchdown velocity

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Created Touchdown velocity for given stall velocity

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1 More Landing Calculators

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Created Aircraft forward velocity for given normal component of side velocity

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Created Aircraft sideslip velocity for given dihedral angle

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Created Dihedral angle for given sideslip velocity

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Created Normal component of aircraft side velocity for given dihedral angle

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Created Normal component of aircraft side velocity for given forward velocity

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Verified Lift Coefficient for Rotating Cylinder with Circulation

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Verified Lift Coefficient for Rotating Cylinder with Tangential Speed

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Verified Lift Force on Cylinder for Circulation

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Verified Radius of Cylinder for Lift Coefficient in Rotating Cylinder with Circulation

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Verified Tangential Velocity of Cylinder with Lift Coefficient

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11 More Lift and Circulation Calculators

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Created Coefficient of Drag due to lift

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Created Drag Coefficient for given parasite drag coefficient

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Created Drag Coefficient for given zero-lift drag coefficient

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Created Parasite Drag Coefficient at zero lift

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17 More Lift and Drag Polar Calculators

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Created Coefficient of Drag due to Lift for Minimum Power required

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Created Coefficient of Drag for given Thrust and Weight

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Created Coefficient of Drag for given Thrust-to-Weight Ratio

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Created Coefficient of Lift for given thrust and weight

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Created Coefficient of Lift for given Thrust-to-Weight Ratio

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Created Drag for Level and Unaccelerated Flight

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Created Drag for Level and Unaccelerated Flight at Negligible Thrust Angle

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Created Freestream Velocity given required Power

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Created Freestream Velocity given Total Drag Force

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Created Lift Coefficient given Minimum required Thrust

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Created Lift for Level and Unaccelerated Flight at Negligible Thrust Angle

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Created Lift for Unaccelerated Flight

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Created Lift-Induced Drag Coefficient given required Thrust

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Created Lift-to-Drag Ratio given required Thrust of Aircraft

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Created Total Drag Force given required Power

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Created Zero-lift drag coefficient at minimum required thrust

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Created Zero-Lift Drag Coefficient for given Lift Coefficient

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Created Zero-Lift Drag Coefficient for Minimum Power required

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Created Zero-Lift Drag Coefficient given required Thrust

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Verified Location of Stagnation Point Outside Cylinder for Lifting Flow

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Verified Radial Velocity for Lifting Flow over Circular Cylinder

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Verified Surface Pressure Coefficient for Lifting Flow over Circular Cylinder

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7 More Lifting Flow over Cylinder Calculators

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Created Back Rake Angle

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Created Inclination Angle

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Created Orthogonal Rake Angle

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Created Side Rake Angle

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5 More Metal Cutting Tools Calculators

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Verified Radiative Heat Transfer to Surface Stemming from Thermal Radiation

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1 More Modern Design Oriented Code Calculators

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Verified Radius of Cylinder for Non-Lifting Flow

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Verified Stream Function for Non-Lifting Flow over Circular Cylinder

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8 More Nonlifting Flow over Cylinder Calculators

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Created Characteristic Mach Number

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Created Downstream Velocity using Prandtl Relation

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Created Relation between Mach Number and Characteristic Mach Number

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4 More Normal Shock Relations Calculators

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Created Component of Downstream Mach Normal to Oblique Shock

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Created Component of Upstream Mach Normal to Oblique Shock

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Created Flow Deflection Angle due to Oblique Shock

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7 More Oblique Shock Calculators

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Created Dynamic Pressure for given Specific Heat Ratio and Mach Number

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Verified Velocity of Sound using Dynamic Pressure and Density

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13 More Oblique Shock Relation Calculators

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Created Friction Coefficient

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20 More Others and Extra Calculators

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Verified Coefficient of Drag Equation using Energy Released from Blast Wave

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7 More Planar and Blunt Slab Blast Wave Calculators

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Created Power required at Altitude

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Created Power required at Altitude given Power at sea-level

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Created Power required at sea-level conditions

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Created Velocity at Altitude

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Created Velocity at Altitude given Velocity at Sea-Level

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Created Velocity at Sea-Level given Lift Coefficient

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11 More Preliminary Aerodynamics Calculators

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Verified Intensity of pressure wave produced for gradual closure of valves

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Verified Loss of Head due to Bend in Pipe

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Verified Loss of head due to sudden enlargement at any particular section of pipe

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11 More Pressure and Flow Head Calculators

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Created Endurance of Propeller-Driven Airplane

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Created Lift-to-Drag ratio for given Range of Propeller-Driven Airplane

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Created Power Available for Reciprocating Engine-Propeller Combination

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Created Propeller Efficiency for given Endurance of Propeller-Driven Airplane

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Created Propeller Efficiency for given Range and Lift-to-Drag Ratio of Propeller-Driven Airplane

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Created Propeller Efficiency for given Range of Propeller-Driven Airplane

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Created Propeller Efficiency for Reciprocating Engine-Propeller Combination

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Created Range of Propeller-Driven Airplane

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Created Range of Propeller-Driven Airplane for given lift-to-drag ratio

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Created Shaft Brake Power for Reciprocating Engine-Propeller Combination

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Created Specific Fuel Consumption for given Endurance of Propeller-Driven Airplane

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Created Specific Fuel Consumption for given Range and Lift-to-Drag Ratio of Propeller-Driven Airplane

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Created Specific Fuel Consumption for given Range of Propeller-Driven Airplane

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9 More Propeller Driven Airplane Calculators

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Verified Density Ratio across Normal Shock

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Created Entropy Change across Normal Shock

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Verified Pressure Ratio across Normal Shock

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Created Shock Strength

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2 More Property Change Across Shock Waves Calculators

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Created Load Factor given Pull-Down Maneuver Radius

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Created Load Factor given Pull-Down Maneuver Rate

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Created Load Factor given Pull-UP Maneuver Radius

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Created Load Factor given Pull-Up Maneuver Rate

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Created Pull-down maneuver radius

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Created Pull-Down Maneuver Rate

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Created Pull-up maneuver radius

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Created Pull-Up Maneuver Rate

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Created Velocity for given Pull-Down Maneuver Rate

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Created Velocity for given Pull-Up Maneuver Radius

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Created Velocity for given Turn Rate for High Load Factor

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Created Velocity given Pull-down Maneuver Radius

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Verified Local Turbulent Skin-Friction Coefficient for Incompressible Flow

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Verified Reynolds Number for Chord Length using Overall Skin-Friction Drag Coefficient

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Verified Turbulent Flat-Plate Skin-Friction Coefficient

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12 More Reference Temperature Method Calculators

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Verified Area of Plane Wall Required for Given Temperature Difference

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Verified Outer Surface Temperature of Wall in Conduction through Wall

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Verified Thermal Conductivity of Material Required to Maintain Given Temperature Difference

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Verified Thickness of Plane Wall for Conduction through Wall

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4 More Single Plane Wall Calculators

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Verified Source Strength for 2-D Incompressible Source Flow

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Verified Stagnation Streamline Equation for Flow over Semi-Infinite Body

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Verified Stream Function for 2-D Incompressible Source Flow

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4 More Source Flow Calculators

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Created Control stick length for given gearing ratio

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Created Elevator Area given Hinge Moment Coefficient

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Created Elevator Area given Stick Force

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Created Elevator Chord Length given Hinge Moment Coefficient

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Created Elevator Chord Length given Stick Force

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Created Elevator Deflection Angle for given Stick Force

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Created Elevator Deflection Angle given Gearing Ratio

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Created Elevator Hinge moment coefficient

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Created Elevator Hinge Moment given Hinge Moment Coefficient

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Created Elevator Stick Force

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Created Elevator Stick Force given Gearing Ratio

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Created Elevator Stick Force given Hinge Moment Coefficient

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Created Flight Velocity for given Stick Force

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Created Flight Velocity given Elevator Hinge Moment Coefficient

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Created Gearing Ratio

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Created Gearing Ratio for given Stick Force

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Created Gearing Ratio given Hinge Moment Coefficient

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Created Hinge Moment Coefficient given Stick Force

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Created Hinge Moment for given Gearing Ratio

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Created Hinge Moment for given Stick Force

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Created Stick Deflection Angle for given Gearing Ratio

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Created Stick Deflection Angle for given Stick Force

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Created Stick Length for given Stick Force

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Created Horizontal tail area for given tail volume ratio

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Created Horizontal tail volume ratio

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Created Horizontal Tail Volume Ratio for given Pitching Moment Coefficient

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Created Mean Aerodynamic Chord for given Tail Pitching Moment Coefficient

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Created Pitching Moment due to Tail

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Created Tail Area for given Tail Moment Coefficient

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Created Tail Efficiency for given Pitching Moment Coefficient

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Created Tail Efficiency for given Tail Volume Ratio

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Created Tail Lift Coefficient for given Tail Volume Ratio

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Created Tail Lift for given Tail Pitching Moment

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Created Tail moment arm for given horizontal tail volume ratio

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Created Tail Moment Arm for given Tail Moment Coefficient

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Created Tail Pitching Moment Coefficient

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Created Tail Pitching Moment Coefficient for given Tail Efficiency

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Created Tail Pitching Moment Coefficient for given Tail Volume Ratio

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Created Tail Pitching Moment for given Lift Coefficient

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Created Tail Pitching Moment for given Moment Coefficient

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Created Wing Mean Aerodynamic Chord for given Horizontal Tail Volume Ratio

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Created Wing Reference Area for given Horizontal Tail Volume Ratio

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Created Coefficient of rolling friction during ground roll

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Created Drag during ground effect

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Created Ground effect factor

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Created Lift acting on aircraft during ground roll

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Created Liftoff distance

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Created Liftoff velocity for given stall velocity

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Created Liftoff velocity for given weight

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Created Maximum Lift coefficient for given liftoff velocity

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Created Maximum Lift coefficient for given stall velocity

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Created Resistance force during ground roll

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Created Stall velocity for given liftoff velocity

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Created Stall velocity for given weight

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Created Thrust for given liftoff distance

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Created Weight of aircraft during ground roll

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1 More Take Off Calculators

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Created Mach Angle

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Created Mach Number

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Created Speed of Sound

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Created Stagnation Temperature

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15 More Thermodynamics and Governing Equations Calculators

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Created Minimum Thrust of aircraft required

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Created Minimum Thrust required for given Lift Coefficient

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Created Minimum Thrust required for given weight

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Created Power required for given aerodynamic coefficients

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Created Power required for given required thrust of aircraft

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Created Power required for given total drag force

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Created Thrust Angle for Unaccelerated Level Flight for given Drag

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Created Thrust Angle for Unaccelerated Level Flight for given Lift

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Created Thrust for given coefficients of lift and drag

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Created Thrust for Level and Unaccelerated Flight

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Created Thrust of aircraft required for given Lift-to-drag ratio

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Created Thrust of Aircraft required for given required Power

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Created Thrust of Aircraft required for Level, Unaccelerated Flight

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Created Thrust-to-weight ratio

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Created Weight of Aircraft for given Coefficients of Lift and Drag

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Created Weight of Aircraft for given Lift-to-Drag Ratio

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Created Weight of aircraft for given required power

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Created Weight of Aircraft for Level, Unaccelerated Flight at Negligible Thrust Angle

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Created Weight of Aircraft in Level, Unaccelerated Flight

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Verified Discharge through Pipe given Head Loss in Turbulent Flow

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Verified Head Loss due to Friction given Power Required in Turbulent Flow

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16 More Turbulent Flow Calculators

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Created Bank angle during level turn

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Created Lift during level turn

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Created Lift for given Load Factor

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Created Load factor given Lift Force and Weight of Aircraft

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Created Load Factor given Turn Radius

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Created Load Factor given Turn Rate

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Created Turn radius

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Created Turn rate

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Created Velocity for given turn radius

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Created Velocity for given turn rate

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Created Weight for given Load Factor

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Created Weight of aircraft during level turn

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1 More Turning Flight Calculators

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Verified Velocity Potential for Uniform Incompressible Flow

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3 More Uniform Flow Calculators

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Verified Density ahead of Normal Shock using Normal Shock Momentum Equation

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Verified Static Pressure ahead of Normal Shock using Normal Shock Momentum Equation

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Verified Velocity ahead of Normal Shock from Normal Shock Energy Equation

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4 More Upstream Shock Waves Calculators

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Verified Coefficient of Velocity given Head Loss

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Verified Theoretical velocity

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Verified Time of Emptying Circular Horizontal Tank

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5 More Velocity and Time Calculators

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Created Moment Produced by Vertical Tail for given Lift Curve Slope

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Created Moment Produced by Vertical Tail for given Moment Coefficient

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Created Moment Produced by Vertical Tail for given Side Force

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Created Vertical Tail Angle of Attack

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Created Vertical Tail Angle of Attack for given Vertical Tail Side Force

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Created Vertical Tail Area for given Moment

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Created Vertical Tail Area for given Vertical Tail Side Force

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Created Vertical tail area for given vertical tail volume ratio

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Created Vertical Tail Area for given Yawing Moment Coefficient

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Created Vertical Tail Dynamic Pressure for given Vertical Tail Side Force

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Created Vertical Tail Efficiency

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Created Vertical Tail Efficiency for given Yawing Moment Coefficient

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Created Vertical Tail Lift Curve Slope

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Created Vertical Tail Lift Curve Slope for Given Moment

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Created Vertical Tail Lift Curve Slope for given Vertical Tail Efficiency

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Created Vertical Tail Lift Curve Slope for given Yawing Moment Coefficient

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Created Vertical Tail Moment Arm for given Lift Curve Slope

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Created Vertical Tail Moment Arm for given Side Force

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Created Vertical Tail Moment Arm for given Vertical Tail Volume Ratio

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Created Vertical Tail Moment Arm for Given Yawing Moment Coefficient

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Created Vertical Tail Side Force

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Created Vertical Tail Side Force for Given Moment

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Created Vertical tail volume ratio

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Created Vertical Tail Volume Ratio for given Yawing Moment Coefficient

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Verified Recovery Factor Calculation using Prandtl Number

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Verified Recovery Factor for Flat Plate with Viscous Flow

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Verified Skin-Friction Drag Coefficient

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12 More Viscous Flow Calculators

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Verified Velocity Potential for 2-D Vortex Flow

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2 More Vortex Flow Calculators

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Verified Wall Temperature over Flat Plate under Viscous, Very High Mach Flow

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3 More Wall Temperature Calculators

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Created Angle of Attack at Tail

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Created Angle of Attack of Wing

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Created Angle of incidence of tail

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Created Angle of incidence of wing

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Created Downwash angle

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Created Lift due to Tail only

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Created Lift due to Wing only

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Created Tail area for given tail efficiency

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Created Tail Efficiency for given lift coefficients

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Created Tail Lift Coefficient for given Pitching Moment

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Created Tail Lift Coefficient for given Pitching Moment Coefficient

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Created Tail Lift Coefficient of Wing-Tail Combination

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Created Total Lift Coefficient of Wing-Tail Combination

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Created Total Lift of Wing-Tail Combination

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Created Wing Lift Coefficient of wing-tail combination

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Created Dynamic Pressure at Vertical Tail for given Vertical Tail Efficiency

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Created Dynamic Pressure at Vertical Tail for given Yawing Moment Coefficient

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Created Dynamic Pressure at Wing for given Vertical Tail Efficiency

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Created Dynamic Pressure at Wing for given Yawing Moment Coefficient

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Created Vertical Tail Dynamic Pressure for given Moment

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Created Wing Area for given Moment Produced by Vertical Tail

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Created Wing Area for given Vertical Tail Volume Ratio

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Created Wing Area for given Yawing Moment Coefficient

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Created Wing Dynamic Pressure for given Yawing Moment Coefficient

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Created Wingspan for given Vertical Tail Volume Ratio

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Created Wingspan for given Yawing Moment Coefficient

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Created Wingspan for Yawing Moment Coefficient given Sideslip Angle and Sidewash Angle

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List of Calculators by Vinay Mishra