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
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
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
Ratio of Stagnation and Static Temperature
Stagnation to Static Temperature=1+(((Specific Heat Ratio-1)/2)*(Mach Number^2)) GO
Dynamic pressure for given specific heat ratio and Mach number
Dynamic Pressure=Specific heat ratio*Static pressure*(Mach Number^2)/2 GO
Mach Angle
Mach Angle=asin(1/Mach Number) GO

1 Other formulas that calculate the same Output

Similarity constant equation with slenderness ratio
Hypersonic similarity parameter=Mach Number*Slenderness Ratio GO

Hypersonic similarity parameter Formula

Hypersonic similarity parameter=Mach Number*Flow Deflection angle
K=M*θ
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Drag force GO
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Moment coefficient GO
Shear-stress distribution. GO
Axial force coefficient GO
Fourier’s law of heat conduction GO
Coefficient of pressure with similarity parameters 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 similarity parameter

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

How to Calculate Hypersonic similarity parameter?

Hypersonic similarity parameter calculator uses Hypersonic similarity parameter=Mach Number*Flow Deflection angle to calculate the Hypersonic similarity parameter, The Hypersonic similarity parameter formula is defined as product of inlet Mach number and the flow deflection angle. Hypersonic similarity parameter and is denoted by K symbol.

How to calculate Hypersonic similarity parameter using this online calculator? To use this online calculator for Hypersonic similarity parameter, enter Mach Number (M) and Flow Deflection angle (θ) and hit the calculate button. Here is how the Hypersonic similarity parameter calculation can be explained with given input values -> 0.53 = 1*30.3667631419393.

FAQ

What is Hypersonic similarity parameter?
The Hypersonic similarity parameter formula is defined as product of inlet Mach number and the flow deflection angle and is represented as K=M*θ or Hypersonic similarity parameter=Mach Number*Flow Deflection angle. Mach number is a dimensionless quantity representing the ratio of flow velocity past a boundary to the local speed of sound and Flow Deflection angle is defined as the angle by which the flow turns towards the oblique shock.
How to calculate Hypersonic similarity parameter?
The Hypersonic similarity parameter formula is defined as product of inlet Mach number and the flow deflection angle is calculated using Hypersonic similarity parameter=Mach Number*Flow Deflection angle. To calculate Hypersonic similarity parameter, you need Mach Number (M) and Flow Deflection angle (θ). With our tool, you need to enter the respective value for Mach Number and Flow Deflection 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 Hypersonic similarity parameter?
In this formula, Hypersonic similarity parameter uses Mach Number and Flow Deflection angle. We can use 1 other way(s) to calculate the same, which is/are as follows -
  • Hypersonic similarity parameter=Mach Number*Slenderness Ratio
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