Sanjay Krishna
Amrita School of Engineering (ASE), Vallikavu
Sanjay Krishna has created this Calculator and 200+ 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
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
Relation between Characteristic Mach number and Mach number
Characteristic Mach number=((Specific heat ratio+1)/((Specific heat ratio-1)+(2/(Mach Number^2))))^0.5 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
Mach Angle
Mach Angle=asin(1/Mach Number) 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
Modified Newtonian Law
Pressure coefficient=The maximum pressure coefficient*(sin(deflection angle))^2 GO
Exact relation for pressure coefficient behind an oblique shock wave when Mach no. tends to infinite
Pressure coefficient=(4/(Specific Heat Ratio+1))*(sin(Wave 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 Formula

Pressure coefficient=(4/(Specific Heat Ratio+1))*(((sin(Wave angle))^2)-(1/Mach Number^2))
C<sub>p</sub>=(4/(γ+1))*(((sin(β))^2)-(1/M^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 when Mach no. tends to infinite 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 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 Exact relation for pressure coefficient behind an oblique shock wave?

Exact relation for pressure coefficient behind an 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, The Exact relation for pressure coefficient behind an oblique shock wave formula is defined as is the interrelation between specific heat ratio and Mach Number. Pressure coefficient and is denoted by Cp symbol.

How to calculate Exact relation for pressure coefficient behind an oblique shock wave using this online calculator? To use this online calculator for Exact relation for pressure coefficient behind an oblique shock wave, enter Specific Heat Ratio (γ), Wave angle (β) and Mach Number (M) and hit the calculate button. Here is how the Exact relation for pressure coefficient behind an oblique shock wave calculation can be explained with given input values -> -1.492071 = (4/(1.6+1))*(((sin(10))^2)-(1/1^2)).

FAQ

What is Exact relation for pressure coefficient behind an oblique shock wave?
The Exact relation for pressure coefficient behind an oblique shock wave formula is defined as is the interrelation between specific heat ratio and Mach Number and is represented as Cp=(4/(γ+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 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, Wave angle is the shock angle created by the oblique shock, this is not similar to the mach angle and Mach number is a dimensionless quantity representing the ratio of flow velocity past a boundary to the local speed of sound.
How to calculate Exact relation for pressure coefficient behind an oblique shock wave?
The Exact relation for pressure coefficient behind an oblique shock wave formula is defined as is the interrelation between specific heat ratio and Mach Number is calculated using Pressure coefficient=(4/(Specific Heat Ratio+1))*(((sin(Wave angle))^2)-(1/Mach Number^2)). To calculate Exact relation for pressure coefficient behind an oblique shock wave, you need Specific Heat Ratio (γ), Wave angle (β) and Mach Number (M). With our tool, you need to enter the respective value for Specific Heat Ratio, Wave angle and 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 and Mach Number. 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
  • 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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