Hypersonic Similarity Parameter Solution

STEP 0: Pre-Calculation Summary
Formula Used
Hypersonic Similarity Parameter = Mach Number*Flow Deflection angle
K = M*θ
This formula uses 3 Variables
Variables Used
Hypersonic Similarity Parameter - (Measured in Radian) - 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.
Mach Number - Mach number is a dimensionless quantity representing the ratio of flow velocity past a boundary to the local speed of sound.
Flow Deflection angle - (Measured in Radian) - Flow Deflection angle is defined as the angle by which the flow turns towards the oblique shock.
STEP 1: Convert Input(s) to Base Unit
Mach Number: 8 --> No Conversion Required
Flow Deflection angle: 0.53 Radian --> 0.53 Radian No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
K = M*θ --> 8*0.53
Evaluating ... ...
K = 4.24
STEP 3: Convert Result to Output's Unit
4.24 Radian --> No Conversion Required
FINAL ANSWER
4.24 Radian <-- Hypersonic Similarity Parameter
(Calculation completed in 00.004 seconds)

Credits

Created by Sanjay Krishna
Amrita School of Engineering (ASE), Vallikavu
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National Institute Of Technology (NIT), Hamirpur
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20 Hypersonic Flow Parameters Calculators

Coefficient of Pressure with Similarity Parameters
Go 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 Ratio having High Mach Number with Similarity Constant
Go Pressure Ratio = (1-((Specific Heat Ratio-1)/2)*Hypersonic Similarity Parameter)^(2*Specific Heat Ratio/(Specific Heat Ratio-1))
Mach Number with Fluids
Go Mach Number = Fluid Velocity/(sqrt(Specific Heat Ratio*Universal Gas Constant*Final Temperature))
Pressure Ratio for High Mach Number
Go Pressure Ratio = (Mach Number ahead of shock/Mach Number behind shock)^(2*Specific Heat Ratio/(Specific Heat Ratio-1))
Moment Coefficient
Go Moment Coefficient = Moment/(Dynamic Pressure*Area for Flow*Chord Length)
Deflection Angle
Go Deflection Angle = 2/(Specific Heat Ratio-1)*(1/Mach Number ahead of shock-1/Mach Number behind shock)
Normal Force Coefficient
Go Coefficient of Force = Normal Force/(Dynamic Pressure*Area for Flow)
Supersonic Expression for Pressure Coefficient on Surface with Local Deflection Angle
Go Pressure Coefficient = (2*Deflection Angle)/(sqrt(Mach Number^2-1))
Dynamic Pressure given Coefficient of Lift
Go Dynamic Pressure = Lift Force/(Lift Coefficient*Area for Flow)
Coefficient of Drag
Go Drag Coefficient = Drag Force/(Dynamic Pressure*Area for Flow)
Dynamic Pressure
Go Dynamic Pressure = Drag Force/(Drag Coefficient*Area for Flow)
Lift Coefficient
Go Lift Coefficient = Lift Force/(Dynamic Pressure*Area for Flow)
Axial Force Coefficient
Go Coefficient of Force = Force/(Dynamic Pressure*Area for Flow)
Drag Force
Go Drag Force = Drag Coefficient*Dynamic Pressure*Area for Flow
Lift Force
Go Lift Force = Lift Coefficient*Dynamic Pressure*Area for Flow
Mach Ratio at High Mach Number
Go Mach Ratio = 1-Hypersonic Similarity Parameter*((Specific Heat Ratio-1)/2)
Hypersonic Similarity Parameter
Go Hypersonic Similarity Parameter = Mach Number*Flow Deflection angle
Shear-Stress Distribution
Go Shear Stress = Viscosity Coefficient*Velocity Gradient
Fourier's Law of Heat Conduction
Go Heat Flux = Thermal Conductivity*Temperature Gradient
Newtonian Sine Squared Law for Pressure Coefficient
Go Pressure Coefficient = 2*sin(Deflection Angle)^2

Hypersonic Similarity Parameter Formula

Hypersonic Similarity Parameter = Mach Number*Flow Deflection angle
K = M*θ

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 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) & Flow Deflection angle (θ) and hit the calculate button. Here is how the Hypersonic Similarity Parameter calculation can be explained with given input values -> 4.24 = 8*0.53.

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 & 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) & Flow Deflection angle (θ). With our tool, you need to enter the respective value for Mach Number & Flow Deflection angle and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.
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