Pressure Ratio of Blunt-Nosed Cylinder (First Approximation) Calculator

✖Mach number Cylinder is a dimensionless quantity representing the ratio of flow velocity past a boundary to the local speed of sound.ⓘ Mach Number Cylinder [M_cylinder]			+10% -10%
✖Drag Coefficient is a dimensionless quantity that is used to quantify the drag or resistance of an object in a fluid environment, such as air or water.ⓘ Drag Coefficient [C_D]			+10% -10%
✖Distance from X-Axis is defined as the distance from the point where stress is to be computed to XX axis.ⓘ Distance from X-Axis [y]			+10% -10%
✖Diameter is a straight line passing from side to side through the center of a body or figure, especially a circle or sphere.ⓘ Diameter [d]			+10% -10%

✖Pressure Ratio is ratio of final to initial pressure.ⓘ Pressure Ratio of Blunt-Nosed Cylinder (First Approximation) [r_p]

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Pressure Ratio of Blunt-Nosed Cylinder (First Approximation) Solution

STEP 0: Pre-Calculation Summary

Formula Used

Pressure Ratio = 0.067*Mach Number Cylinder^2*sqrt(Drag Coefficient)/(Distance from X-Axis/Diameter)
r_p = 0.067*M_cylinder^2*sqrt(C_D)/(y/d)
This formula uses 1 Functions, 5 Variables

Functions Used

sqrt - A square root function is a function that takes a non-negative number as an input and returns the square root of the given input number., sqrt(Number)

Variables Used

Pressure Ratio - Pressure Ratio is ratio of final to initial pressure.
Mach Number Cylinder - Mach number Cylinder is a dimensionless quantity representing the ratio of flow velocity past a boundary to the local speed of sound.
Drag Coefficient - Drag Coefficient is a dimensionless quantity that is used to quantify the drag or resistance of an object in a fluid environment, such as air or water.
Distance from X-Axis - (Measured in Meter) - Distance from X-Axis is defined as the distance from the point where stress is to be computed to XX axis.
Diameter - (Measured in Meter) - Diameter is a straight line passing from side to side through the center of a body or figure, especially a circle or sphere.

STEP 1: Convert Input(s) to Base Unit

Mach Number Cylinder: 3.7 --> No Conversion Required
Drag Coefficient: 3.4 --> No Conversion Required
Distance from X-Axis: 2200 Millimeter --> 2.2 Meter (Check conversion here)
Diameter: 1223 Millimeter --> 1.223 Meter (Check conversion here)

STEP 2: Evaluate Formula

Substituting Input Values in Formula

r_p = 0.067*M_cylinder^2*sqrt(C_D)/(y/d) --> 0.067*3.7^2*sqrt(3.4)/(2.2/1.223)

Evaluating ... ...

r_p = 0.940202681692205

STEP 3: Convert Result to Output's Unit

0.940202681692205 --> No Conversion Required

FINAL ANSWER

0.940202681692205 ≈ 0.940203 <-- Pressure Ratio

(Calculation completed in 00.004 seconds)

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Amrita School of Engineering (ASE), Vallikavu

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< Hypersonic Flight Paths Velocity of Altitude Map Calculators

Forces Acting Perpendicular to Body on Flight Path

LaTeX Go Lift Force = Weight*cos(Angle of Inclination)-Mass*(Velocity^2)/Radius

Forces Acting on Body along Flight Path

LaTeX Go Drag force along flight path = Weight*sin(Angle of Inclination)-Mass*Velocity Gradient

Radius for Cylinder-Wedge Body Shape

LaTeX Go Radius = Radius of Curvature/(1.386*exp(1.8/(Mach Number-1)^0.75))

Radius for Sphere-Cone Body Shape

LaTeX Go Radius = Radius of Curvature/(1.143*exp(0.54/(Mach Number-1)^1.2))

Pressure Ratio of Blunt-Nosed Cylinder (First Approximation) Formula

LaTeX Go

Pressure Ratio = 0.067*Mach Number Cylinder^2*sqrt(Drag Coefficient)/(Distance from X-Axis/Diameter)
r_p = 0.067*M_cylinder^2*sqrt(C_D)/(y/d)

What is blast wave?

In fluid dynamics, a blast wave is the increased pressure and flow resulting from the deposition of a large amount of energy in a small, very localised volume.

How to Calculate Pressure Ratio of Blunt-Nosed Cylinder (First Approximation)?

Pressure Ratio of Blunt-Nosed Cylinder (First Approximation) calculator uses Pressure Ratio = 0.067*Mach Number Cylinder^2*sqrt(Drag Coefficient)/(Distance from X-Axis/Diameter) to calculate the Pressure Ratio, Pressure Ratio of Blunt-Nosed Cylinder (First Approximation) formula is defined as a dimensionless quantity used to characterize the aerodynamic performance of a blunt-nosed cylinder in hypersonic flight, providing a crucial parameter for velocity of altitude map in hypersonic flight paths. Pressure Ratio is denoted by r_p symbol.

How to calculate Pressure Ratio of Blunt-Nosed Cylinder (First Approximation) using this online calculator? To use this online calculator for Pressure Ratio of Blunt-Nosed Cylinder (First Approximation), enter Mach Number Cylinder (M_cylinder), Drag Coefficient (C_D), Distance from X-Axis (y) & Diameter (d) and hit the calculate button. Here is how the Pressure Ratio of Blunt-Nosed Cylinder (First Approximation) calculation can be explained with given input values -> 0.940203 = 0.067*3.7^2*sqrt(3.4)/(2.2/1.223).

FAQ

What is Pressure Ratio of Blunt-Nosed Cylinder (First Approximation)?

Pressure Ratio of Blunt-Nosed Cylinder (First Approximation) formula is defined as a dimensionless quantity used to characterize the aerodynamic performance of a blunt-nosed cylinder in hypersonic flight, providing a crucial parameter for velocity of altitude map in hypersonic flight paths and is represented as r_p = 0.067*M_cylinder^2*sqrt(C_D)/(y/d) or Pressure Ratio = 0.067*Mach Number Cylinder^2*sqrt(Drag Coefficient)/(Distance from X-Axis/Diameter). Mach number Cylinder is a dimensionless quantity representing the ratio of flow velocity past a boundary to the local speed of sound, Drag Coefficient is a dimensionless quantity that is used to quantify the drag or resistance of an object in a fluid environment, such as air or water, Distance from X-Axis is defined as the distance from the point where stress is to be computed to XX axis & Diameter is a straight line passing from side to side through the center of a body or figure, especially a circle or sphere.

How to calculate Pressure Ratio of Blunt-Nosed Cylinder (First Approximation)?

Pressure Ratio of Blunt-Nosed Cylinder (First Approximation) formula is defined as a dimensionless quantity used to characterize the aerodynamic performance of a blunt-nosed cylinder in hypersonic flight, providing a crucial parameter for velocity of altitude map in hypersonic flight paths is calculated using Pressure Ratio = 0.067*Mach Number Cylinder^2*sqrt(Drag Coefficient)/(Distance from X-Axis/Diameter). To calculate Pressure Ratio of Blunt-Nosed Cylinder (First Approximation), you need Mach Number Cylinder (M_cylinder), Drag Coefficient (C_D), Distance from X-Axis (y) & Diameter (d). With our tool, you need to enter the respective value for Mach Number Cylinder, Drag Coefficient, Distance from X-Axis & Diameter and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

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