Sanjay Krishna
Amrita School of Engineering (ASE), Vallikavu
Sanjay Krishna has created this Calculator and 200+ more calculators!
Maiarutselvan V
PSG College of Technology (PSGCT), Coimbatore
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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
Component of Downstream Mach normal to oblique shock
Downstream mach normal to oblique shock=Mach Number behind shock*sin(Oblique shock angle-Flow Deflection angle) 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 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
Pressure coefficient=2*(sin(Wave angle))^2 GO

Coefficient of pressure with similarity parameters Formula

Pressure coefficient=(2*(Flow Deflection angle)^2)*(((Specific Heat Ratio+1)/4)+sqrt((((Specific Heat Ratio+1)/4)^2)+(1/(Hypersonic similarity parameter)^2)))
C<sub>p</sub>=(2*(θ)^2)*(((γ+1)/4)+sqrt((((γ+1)/4)^2)+(1/(K)^2)))
More formulas
Mach number GO
Dynamic pressure GO
lift coefficient GO
Lift Force GO
Coefficient of drag GO
Drag force GO
Dynamic pressure based on coefficient of lift GO
Normal Force Coefficient GO
Deflection angle GO
Moment coefficient GO
Shear-stress distribution. GO
Axial force coefficient GO
Fourier’s law of heat conduction GO
Hypersonic similarity parameter GO
Pressure ratio for high Mach number GO
Mach ratio at high mach number GO
Pressure ratio having high mach number with similarity constant GO
Newtonian sine-squared law for pressure coefficient GO
Supersonic expression for pressure coefficient on a surface with local deflection angle θ GO

What is a similarity parameter?

Similarity parameters mean some independent dimensionless parameter groups that represent the quantitative characteristics of physical similarity.

How to Calculate Coefficient of pressure with similarity parameters?

Coefficient of pressure with similarity parameters calculator uses Pressure coefficient=(2*(Flow Deflection angle)^2)*(((Specific Heat Ratio+1)/4)+sqrt((((Specific Heat Ratio+1)/4)^2)+(1/(Hypersonic similarity parameter)^2))) to calculate the Pressure coefficient, Coefficient of pressure with similarity parameters formula is the interrelation of similarity parameters of hypersonic flaw and deflection angle. Pressure coefficient and is denoted by Cp symbol.

How to calculate Coefficient of pressure with similarity parameters using this online calculator? To use this online calculator for Coefficient of pressure with similarity parameters, enter Flow Deflection angle (θ), Specific Heat Ratio (γ) and Hypersonic similarity parameter (K) and hit the calculate button. Here is how the Coefficient of pressure with similarity parameters calculation can be explained with given input values -> 1.546621 = (2*(0.53)^2)*(((1.6+1)/4)+sqrt((((1.6+1)/4)^2)+(1/(0.5)^2))).

FAQ

What is Coefficient of pressure with similarity parameters?
Coefficient of pressure with similarity parameters formula is the interrelation of similarity parameters of hypersonic flaw and deflection angle and is represented as Cp=(2*(θ)^2)*(((γ+1)/4)+sqrt((((γ+1)/4)^2)+(1/(K)^2))) or Pressure coefficient=(2*(Flow Deflection angle)^2)*(((Specific Heat Ratio+1)/4)+sqrt((((Specific Heat Ratio+1)/4)^2)+(1/(Hypersonic similarity parameter)^2))). Flow Deflection angle is defined as the angle by which the flow turns towards the oblique shock, 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 Hypersonic similarity parameter, In the study of hypersonic flow over slender bodies, the product M1u is an important governing parameter, where, as before. It is to simplify the equations.
How to calculate Coefficient of pressure with similarity parameters?
Coefficient of pressure with similarity parameters formula is the interrelation of similarity parameters of hypersonic flaw and deflection angle is calculated using Pressure coefficient=(2*(Flow Deflection angle)^2)*(((Specific Heat Ratio+1)/4)+sqrt((((Specific Heat Ratio+1)/4)^2)+(1/(Hypersonic similarity parameter)^2))). To calculate Coefficient of pressure with similarity parameters, you need Flow Deflection angle (θ), Specific Heat Ratio (γ) and Hypersonic similarity parameter (K). With our tool, you need to enter the respective value for Flow Deflection angle, Specific Heat Ratio and Hypersonic similarity parameter 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 Flow Deflection angle, Specific Heat Ratio and Hypersonic similarity parameter. 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*(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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