Pressure Coefficient behind Oblique Shock Wave for Infinite Mach Number Calculator

✖The Specific Heat Ratio is the ratio of the heat capacity at constant pressure to the heat capacity at constant volume, important for understanding fluid behavior in hypersonic flows.ⓘ Specific Heat Ratio [Y]			+10% -10%
✖The Wave Angle is the angle between the direction of a hypersonic flow and the wave generated by an oblique shock in fluid mechanics.ⓘ Wave Angle [β]			+10% -10%

✖The Pressure Coefficient is a dimensionless number that represents the relative pressure difference across a surface in fluid flow, indicating how pressure varies in different flow conditions.ⓘ Pressure Coefficient behind Oblique Shock Wave for Infinite Mach Number [C_p]

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Pressure Coefficient behind Oblique Shock Wave for Infinite Mach Number Solution

STEP 0: Pre-Calculation Summary

Formula Used

Pressure Coefficient = 4/(Specific Heat Ratio+1)*(sin(Wave Angle))^2
C_p = 4/(Y+1)*(sin(β))^2
This formula uses 1 Functions, 3 Variables

Functions Used

sin - Sine is a trigonometric function that describes the ratio of the length of the opposite side of a right triangle to the length of the hypotenuse., sin(Angle)

Variables Used

Pressure Coefficient - The Pressure Coefficient is a dimensionless number that represents the relative pressure difference across a surface in fluid flow, indicating how pressure varies in different flow conditions.
Specific Heat Ratio - The Specific Heat Ratio is the ratio of the heat capacity at constant pressure to the heat capacity at constant volume, important for understanding fluid behavior in hypersonic flows.
Wave Angle - (Measured in Radian) - The Wave Angle is the angle between the direction of a hypersonic flow and the wave generated by an oblique shock in fluid mechanics.

STEP 1: Convert Input(s) to Base Unit

Specific Heat Ratio: 1.6 --> No Conversion Required
Wave Angle: 0.5 Radian --> 0.5 Radian No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_p = 4/(Y+1)*(sin(β))^2 --> 4/(1.6+1)*(sin(0.5))^2

Evaluating ... ...

C_p = 0.353613610870662

STEP 3: Convert Result to Output's Unit

0.353613610870662 --> No Conversion Required

FINAL ANSWER

0.353613610870662 ≈ 0.353614 <-- Pressure Coefficient

(Calculation completed in 00.020 seconds)

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Created by Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

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K J Somaiya College of Engineering (K J Somaiya), Mumbai

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< Oblique Shock Relation Calculators

Parallel Upstream Flow Components after Shock as Mach Tends to Infinite

LaTeX Go Parallel Upstream Flow Components = Velocity of the fluid at 1*(1-(2*(sin(Wave Angle))^2)/(Specific Heat Ratio-1))

Perpendicular Upstream Flow Components behind Shock Wave

LaTeX Go Perpendicular upstream flow components = (Velocity of the fluid at 1*sin(2*Wave Angle))/(Specific Heat Ratio-1)

Wave Angle for Small Deflection Angle

LaTeX Go Wave Angle = (Specific Heat Ratio+1)/2*(Deflection Angle*180/pi)*pi/180

Coefficient of Pressure Derived from Oblique Shock Theory

LaTeX Go Pressure Coefficient = 2*(sin(Wave Angle))^2

Pressure Coefficient behind Oblique Shock Wave for Infinite Mach Number Formula

LaTeX Go

Pressure Coefficient = 4/(Specific Heat Ratio+1)*(sin(Wave Angle))^2
C_p = 4/(Y+1)*(sin(β))^2

What is pressure coefficient?

The pressure coefficient is a dimensionless number which describes the relative pressures throughout a flow field in fluid dynamics. The pressure coefficient is used in aerodynamics and hydrodynamics. Every point in a fluid flow field has its own unique pressure coefficient

How to Calculate Pressure Coefficient behind Oblique Shock Wave for Infinite Mach Number?

Pressure Coefficient behind Oblique Shock Wave for Infinite Mach Number calculator uses Pressure Coefficient = 4/(Specific Heat Ratio+1)*(sin(Wave Angle))^2 to calculate the Pressure Coefficient, Pressure Coefficient behind Oblique Shock Wave for Infinite Mach Number formula is defined as a dimensionless quantity that characterizes the pressure ratio across an oblique shock wave in a supersonic flow, providing a crucial parameter in the analysis of high-speed aerodynamics and aerospace engineering applications. Pressure Coefficient is denoted by C_p symbol.

How to calculate Pressure Coefficient behind Oblique Shock Wave for Infinite Mach Number using this online calculator? To use this online calculator for Pressure Coefficient behind Oblique Shock Wave for Infinite Mach Number, enter Specific Heat Ratio (Y) & Wave Angle (β) and hit the calculate button. Here is how the Pressure Coefficient behind Oblique Shock Wave for Infinite Mach Number calculation can be explained with given input values -> 0.353614 = 4/(1.6+1)*(sin(0.5))^2.

FAQ

What is Pressure Coefficient behind Oblique Shock Wave for Infinite Mach Number?

Pressure Coefficient behind Oblique Shock Wave for Infinite Mach Number formula is defined as a dimensionless quantity that characterizes the pressure ratio across an oblique shock wave in a supersonic flow, providing a crucial parameter in the analysis of high-speed aerodynamics and aerospace engineering applications and is represented as C_p = 4/(Y+1)*(sin(β))^2 or Pressure Coefficient = 4/(Specific Heat Ratio+1)*(sin(Wave Angle))^2. The Specific Heat Ratio is the ratio of the heat capacity at constant pressure to the heat capacity at constant volume, important for understanding fluid behavior in hypersonic flows & The Wave Angle is the angle between the direction of a hypersonic flow and the wave generated by an oblique shock in fluid mechanics.

How to calculate Pressure Coefficient behind Oblique Shock Wave for Infinite Mach Number?

Pressure Coefficient behind Oblique Shock Wave for Infinite Mach Number formula is defined as a dimensionless quantity that characterizes the pressure ratio across an oblique shock wave in a supersonic flow, providing a crucial parameter in the analysis of high-speed aerodynamics and aerospace engineering applications is calculated using Pressure Coefficient = 4/(Specific Heat Ratio+1)*(sin(Wave Angle))^2. To calculate Pressure Coefficient behind Oblique Shock Wave for Infinite Mach Number, you need Specific Heat Ratio (Y) & Wave Angle (β). With our tool, you need to enter the respective value for Specific Heat Ratio & Wave Angle and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

How many ways are there to calculate Pressure Coefficient?

In this formula, Pressure Coefficient uses Specific Heat Ratio & Wave Angle. We can use 3 other way(s) to calculate the same, which is/are as follows -

Pressure Coefficient = 2*(sin(Wave Angle))^2
Pressure Coefficient = 4/(Specific Heat Ratio+1)*((sin(Wave Angle))^2-1/Mach Number^2)
Pressure Coefficient = Change in Static Pressure/Dynamic Pressure

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