Exact relation for pressure coefficient behind an oblique shock wave when Mach no. tends to infinite Calculator

Category	Engineering ↺
Engineering	Mechanical ↺
Mechanical	Fluid Mechanics ↺
Fluid-Mechanics	Hypersonic Flow ↺
Hypersonic-Flow	oblique shock relation ↺

✖The Specific heat ratio of a gas is the ratio of the specific heat of the gas at a constant pressure to its specific heat at a constant volumeⓘ Specific Heat Ratio [γ]			+10% -10%
✖Wave angle is the shock angle created by the oblique shock, this is not similar to the mach angleⓘ Wave angle [β]			+10% -10%

✖Pressure coefficient defines the value of local pressure at a point in terms of free stream pressure and dynamic pressure.ⓘ Exact relation for pressure coefficient behind an oblique shock wave when Mach no. tends to infinite [C_p]

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Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

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

Rushi Shah

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

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< 11 Other formulas that you can solve using the same Inputs

Exact Density Ratio

Density ratio=((Specific Heat Ratio+1)*((Mach Number*(sin(Wave angle)))^2))/((Specific Heat Ratio-1)*((Mach Number*(sin(Wave angle)))^2)+2) GO

Temperature ratio when Mach becomes infinite

Temperature Ratio=(2*Specific Heat Ratio*(Specific Heat Ratio-1))*((Mach Number*sin(Wave angle))^2)/(Specific Heat Ratio+1)^2 GO

Ratio of stagnation and static pressure

Stagnation to Static Pressure=(1+(((Specific Heat Ratio-1)/2)*(Mach Number^2)))^(Specific Heat Ratio/(Specific Heat Ratio-1)) GO

Ratio of Stagnation and Static Density

Stagnation to Static Density=(1+(((Specific Heat Ratio-1)/2)*(Mach Number^2)))^(1/(Specific Heat Ratio-1)) GO

Deflection angle

deflection angle=(2/(Specific Heat Ratio-1))*((1/Mach Number ahead of shock)-(1/Mach Number behind shock)) GO

Exact pressure ratio

pressure ratio=1+(2*Specific Heat Ratio/(Specific Heat Ratio+1))*(((Mach Number*sin(Wave angle))^2)-1) GO

Pressure ratio when Mach becomes infinite

pressure ratio=(2*Specific Heat Ratio/(Specific Heat Ratio+1))*((Mach Number*sin(Wave angle))^2) GO

Mach number

Mach Number=Fluid Velocity/(sqrt(Specific Heat Ratio*Universal Gas Constant*final temp.)) GO

Ratio of Stagnation and Static Temperature

Stagnation to Static Temperature=1+(((Specific Heat Ratio-1)/2)*(Mach Number^2)) GO

Speed of Sound

Speed of Sound=sqrt(Specific Heat Ratio*[R-Dry-Air]*Temperature of Gas) GO

Density ratio when Mach become infinite

Density ratio=(Specific Heat Ratio+1)/(Specific Heat Ratio-1) GO

< 11 Other formulas that calculate the same Output

Coefficient of pressure with similarity parameters

Pressure coefficient=(2*(Flow Deflection angle)^2)*(((Specific Heat Ratio+1)/4)+sqrt((((Specific Heat Ratio+1)/4)^2)+(1/(Hypersonic similarity parameter)^2))) GO

Coefficient of pressure with slenderness ratio

Pressure coefficient=(2/Specific Heat Ratio*Mach Number^2)*(Non-dimensionalized Pressure*Specific Heat Ratio*(Mach Number^2)*(Slenderness Ratio^2)-1) GO

Coefficient of pressure with slenderness ratio

Pressure coefficient=2*(Slenderness Ratio^2)*(Non-dimensionalized Pressure-(1/(Specific Heat Ratio*(Mach Number^2)*(Slenderness Ratio^2)))) GO

Pressure coefficient for slender bodies of revolution

Pressure coefficient=2*(Angle of Deflection^2)+(Curvature of the surface *Distance of Point from Centroidal Axis) GO

Pressure coefficient for slender 2-D bodies

Pressure coefficient=2*((deflection angle^2)+(Curvature of the surface *Distance of Point from Centroidal Axis)) GO

Exact relation for pressure coefficient behind an oblique shock wave

Pressure coefficient=(4/(Specific Heat Ratio+1))*(((sin(Wave angle))^2)-(1/Mach Number^2)) GO

Modified Newtonian Law

Pressure coefficient=The maximum pressure coefficient*(sin(deflection angle))^2 GO

Supersonic expression for pressure coefficient on a surface with local deflection angle θ

Pressure coefficient=(2*deflection angle)/(sqrt(Mach Number^2-1)) GO

Non-dimensional pressure coefficient

Pressure coefficient=Change in static pressure/Dynamic Pressure GO

Newtonian sine-squared law for pressure coefficient

Pressure coefficient=2*(sin(deflection angle))^2 GO

Coefficient of pressure derived from oblique shock theory

Pressure coefficient=2*(sin(Wave angle))^2 GO

Exact relation for pressure coefficient behind an oblique shock wave when Mach no. tends to infinite Formula

Pressure coefficient=(4/(Specific Heat Ratio+1))*(sin(Wave angle))^2
C<sub>p</sub>=(4/(γ+1))*(sin(β))^2

More formulas

Exact pressure ratio GO

Pressure ratio when Mach becomes infinite GO

Exact Density Ratio GO

Density ratio when Mach become infinite GO

Temperature ratios GO

Temperature ratio when Mach becomes infinite GO

Non-dimensional pressure coefficient GO

Velocity of sound using dynamic pressure and density GO

Dynamic pressure for given specific heat ratio and Mach number GO

Exact relation for pressure coefficient behind an oblique shock wave GO

Wave angle for small deflection angle GO

Coefficient of pressure derived from oblique shock theory GO

Parallel upstream flow components after shock as Mach tends to infinite GO

Perpendicular upstream flow components behind the shock wave GO

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 Exact relation for pressure coefficient behind an oblique shock wave when Mach no. tends to infinite?

Exact relation for pressure coefficient behind an oblique shock wave when Mach no. tends to infinite calculator uses Pressure coefficient=(4/(Specific Heat Ratio+1))*(sin(Wave angle))^2 to calculate the Pressure coefficient, The Exact relation for pressure coefficient behind an oblique shock wave when Mach no. tends to infinite formula is interrelation between specific heat ratio and sin of wave angle. Pressure coefficient and is denoted by C_p symbol.

How to calculate Exact relation for pressure coefficient behind an oblique shock wave when Mach no. tends to infinite using this online calculator? To use this online calculator for Exact relation for pressure coefficient behind an oblique shock wave when Mach no. tends to infinite, enter Specific Heat Ratio (γ) and Wave angle (β) and hit the calculate button. Here is how the Exact relation for pressure coefficient behind an oblique shock wave when Mach no. tends to infinite calculation can be explained with given input values -> 0.04639 = (4/(1.6+1))*(sin(10))^2.

FAQ

What is Exact relation for pressure coefficient behind an oblique shock wave when Mach no. tends to infinite?

The Exact relation for pressure coefficient behind an oblique shock wave when Mach no. tends to infinite formula is interrelation between specific heat ratio and sin of wave angle and is represented as C_p=(4/(γ+1))*(sin(β))^2 or Pressure coefficient=(4/(Specific Heat Ratio+1))*(sin(Wave angle))^2. The Specific heat ratio of a gas is the ratio of the specific heat of the gas at a constant pressure to its specific heat at a constant volume and Wave angle is the shock angle created by the oblique shock, this is not similar to the mach angle.

How to calculate Exact relation for pressure coefficient behind an oblique shock wave when Mach no. tends to infinite?

The Exact relation for pressure coefficient behind an oblique shock wave when Mach no. tends to infinite formula is interrelation between specific heat ratio and sin of wave angle is calculated using Pressure coefficient=(4/(Specific Heat Ratio+1))*(sin(Wave angle))^2. To calculate Exact relation for pressure coefficient behind an oblique shock wave when Mach no. tends to infinite, you need Specific Heat Ratio (γ) and Wave angle (β). With our tool, you need to enter the respective value for Specific Heat Ratio and 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 and Wave angle. We can use 11 other way(s) to calculate the same, which is/are as follows -

Pressure coefficient=Change in static pressure/Dynamic Pressure
Pressure coefficient=(4/(Specific Heat Ratio+1))*(((sin(Wave angle))^2)-(1/Mach Number^2))
Pressure coefficient=(2*(Flow Deflection angle)^2)*(((Specific Heat Ratio+1)/4)+sqrt((((Specific Heat Ratio+1)/4)^2)+(1/(Hypersonic similarity parameter)^2)))
Pressure coefficient=2*(sin(deflection angle))^2
Pressure coefficient=(2*deflection angle)/(sqrt(Mach Number^2-1))
Pressure coefficient=The maximum pressure coefficient*(sin(deflection angle))^2
Pressure coefficient=2*((deflection angle^2)+(Curvature of the surface *Distance of Point from Centroidal Axis))
Pressure coefficient=2*(Angle of Deflection^2)+(Curvature of the surface *Distance of Point from Centroidal Axis)
Pressure coefficient=2*(sin(Wave angle))^2
Pressure coefficient=2*(Slenderness Ratio^2)*(Non-dimensionalized Pressure-(1/(Specific Heat Ratio*(Mach Number^2)*(Slenderness Ratio^2))))
Pressure coefficient=(2/Specific Heat Ratio*Mach Number^2)*(Non-dimensionalized Pressure*Specific Heat Ratio*(Mach Number^2)*(Slenderness Ratio^2)-1)

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