Pressure Coefficient behind Oblique Shock Wave 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 Mach Number is a dimensionless quantity representing the ratio of the speed of an object to the speed of sound in the surrounding medium.ⓘ Mach Number [M]			+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 [C_p]

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Pressure Coefficient behind Oblique Shock Wave Solution

STEP 0: Pre-Calculation Summary

Formula Used

Pressure Coefficient = 4/(Specific Heat Ratio+1)*((sin(Wave Angle))^2-1/Mach Number^2)
C_p = 4/(Y+1)*((sin(β))^2-1/M^2)
This formula uses 1 Functions, 4 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.
Mach Number - The Mach Number is a dimensionless quantity representing the ratio of the speed of an object to the speed of sound in the surrounding medium.

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
Mach Number: 8 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_p = 4/(Y+1)*((sin(β))^2-1/M^2) --> 4/(1.6+1)*((sin(0.5))^2-1/8^2)

Evaluating ... ...

C_p = 0.3295751493322

STEP 3: Convert Result to Output's Unit

0.3295751493322 --> No Conversion Required

FINAL ANSWER

0.3295751493322 ≈ 0.329575 <-- Pressure Coefficient

(Calculation completed in 00.004 seconds)

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Created by Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

Sanjay Krishna has created this Calculator and 300+ more calculators!

Verified by Rushi Shah

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 Formula

LaTeX Go

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

What is a 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?

Pressure Coefficient behind Oblique Shock Wave calculator uses Pressure Coefficient = 4/(Specific Heat Ratio+1)*((sin(Wave Angle))^2-1/Mach Number^2) to calculate the Pressure Coefficient, Pressure Coefficient behind Oblique Shock Wave formula is defined as a dimensionless quantity that characterizes the pressure ratio across an oblique shock wave, which is a fundamental concept in aerodynamics and plays a crucial role in the analysis of supersonic flows and shock waves in compressible fluids. Pressure Coefficient is denoted by C_p symbol.

How to calculate Pressure Coefficient behind Oblique Shock Wave using this online calculator? To use this online calculator for Pressure Coefficient behind Oblique Shock Wave, enter Specific Heat Ratio (Y), Wave Angle (β) & Mach Number (M) and hit the calculate button. Here is how the Pressure Coefficient behind Oblique Shock Wave calculation can be explained with given input values -> 0.329575 = 4/(1.6+1)*((sin(0.5))^2-1/8^2).

FAQ

What is Pressure Coefficient behind Oblique Shock Wave?

Pressure Coefficient behind Oblique Shock Wave formula is defined as a dimensionless quantity that characterizes the pressure ratio across an oblique shock wave, which is a fundamental concept in aerodynamics and plays a crucial role in the analysis of supersonic flows and shock waves in compressible fluids and is represented as C_p = 4/(Y+1)*((sin(β))^2-1/M^2) or Pressure Coefficient = 4/(Specific Heat Ratio+1)*((sin(Wave Angle))^2-1/Mach Number^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 & The Mach Number is a dimensionless quantity representing the ratio of the speed of an object to the speed of sound in the surrounding medium.

How to calculate Pressure Coefficient behind Oblique Shock Wave?

Pressure Coefficient behind Oblique Shock Wave formula is defined as a dimensionless quantity that characterizes the pressure ratio across an oblique shock wave, which is a fundamental concept in aerodynamics and plays a crucial role in the analysis of supersonic flows and shock waves in compressible fluids is calculated using Pressure Coefficient = 4/(Specific Heat Ratio+1)*((sin(Wave Angle))^2-1/Mach Number^2). To calculate Pressure Coefficient behind Oblique Shock Wave, you need Specific Heat Ratio (Y), Wave Angle (β) & Mach Number (M). With our tool, you need to enter the respective value for Specific Heat Ratio, Wave Angle & Mach Number 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 & Mach Number. 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 = Change in Static Pressure/Dynamic Pressure
Pressure Coefficient = 4/(Specific Heat Ratio+1)*(sin(Wave Angle))^2

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