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
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
Parallel upstream flow components after shock as Mach tends to infinite
Parallel upstream flow components =Velocity_of the fluid at 1*(1-(2*(sin(Wave angle))^2)/(Specific Heat Ratio-1)) GO
Perpendicular upstream flow components behind the shock wave
Perpendicular upstream flow components=Velocity_of the fluid at 1*((sin(2*Wave angle))/(Specific Heat Ratio-1)) GO
Exact pressure ratio
pressure ratio=1+(2*Specific Heat Ratio/(Specific Heat Ratio+1))*(((Mach Number*sin(Wave angle))^2)-1) GO
Non-dimensional parallel velocity component for high mach number
Non dimensionalized upstream parallel velocity=1-((2*(sin(Wave angle))^2)/(Specific Heat Ratio-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
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
Non-dimensional pressure for high mach number
Non-dimensionalized Pressure=(2*(sin(Wave angle)^2))/(Specific Heat Ratio+1) GO
Non-dimensional perpendicular velocity component for high mach number
Non dimensionalized velocity=((sin(2*Wave angle))/(Specific Heat Ratio-1)) 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

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
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 Formula

Pressure coefficient=2*(sin(Wave angle))^2
C<sub>p</sub>=2*(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
Exact relation for pressure coefficient behind an oblique shock wave when Mach no. tends to infinite GO
Wave angle for small deflection angle GO
Parallel upstream flow components after shock as Mach tends to infinite GO
Perpendicular upstream flow components behind the shock wave GO

What is oblique shock?

An oblique shock wave is a shock wave that, unlike a normal shock, is inclined with respect to the incident upstream flow direction. It will occur when a supersonic flow encounters a corner that effectively turns the flow into itself and compresses

How to Calculate Coefficient of pressure derived from oblique shock theory?

Coefficient of pressure derived from oblique shock theory calculator uses Pressure coefficient=2*(sin(Wave angle))^2 to calculate the Pressure coefficient, The Coefficient of pressure derived from oblique shock theory formula is defined as the double of square of sine of wave angle, this is derived from oblique shock theory hence wave angle . Pressure coefficient and is denoted by Cp symbol.

How to calculate Coefficient of pressure derived from oblique shock theory using this online calculator? To use this online calculator for Coefficient of pressure derived from oblique shock theory, enter Wave angle (β) and hit the calculate button. Here is how the Coefficient of pressure derived from oblique shock theory calculation can be explained with given input values -> 0.060307 = 2*(sin(10))^2.

FAQ

What is Coefficient of pressure derived from oblique shock theory?
The Coefficient of pressure derived from oblique shock theory formula is defined as the double of square of sine of wave angle, this is derived from oblique shock theory hence wave angle and is represented as Cp=2*(sin(β))^2 or Pressure coefficient=2*(sin(Wave angle))^2. Wave angle is the shock angle created by the oblique shock, this is not similar to the mach angle.
How to calculate Coefficient of pressure derived from oblique shock theory?
The Coefficient of pressure derived from oblique shock theory formula is defined as the double of square of sine of wave angle, this is derived from oblique shock theory hence wave angle is calculated using Pressure coefficient=2*(sin(Wave angle))^2. To calculate Coefficient of pressure derived from oblique shock theory, you need Wave angle (β). With our tool, you need to enter the respective value for 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 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=(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*(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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