Mach Ratio at High Mach Number Calculator

✖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.ⓘ Hypersonic Similarity Parameter [K]			+10% -10%
✖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.ⓘ Specific Heat Ratio [Y]			+10% -10%

✖Mach Ratio is the ratio of Mach numbers before and after the shock.ⓘ Mach Ratio at High Mach Number [Ma]

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Formula

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Mach Ratio at High Mach Number

Formula

`"Ma" = 1-"K"*(("Y"-1)/2)`

Example

`"0.4"=1-"2rad"*(("1.6"-1)/2)`

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Mach Ratio at High Mach Number Solution

STEP 0: Pre-Calculation Summary

Formula Used

Mach Ratio = 1-Hypersonic Similarity Parameter*((Specific Heat Ratio-1)/2)
Ma = 1-K*((Y-1)/2)
This formula uses 3 Variables

Variables Used

Mach Ratio - Mach Ratio is the ratio of Mach numbers before and after the shock.
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.
Specific Heat Ratio - 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.

STEP 1: Convert Input(s) to Base Unit

Hypersonic Similarity Parameter: 2 Radian --> 2 Radian No Conversion Required
Specific Heat Ratio: 1.6 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

Ma = 1-K*((Y-1)/2) --> 1-2*((1.6-1)/2)

Evaluating ... ...

Ma = 0.4

STEP 3: Convert Result to Output's Unit

0.4 --> No Conversion Required

FINAL ANSWER

0.4 <-- Mach Ratio

(Calculation completed in 00.004 seconds)

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Created by Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

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Verified by Maiarutselvan V

PSG College of Technology (PSGCT), Coimbatore

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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

Mach Ratio at High Mach Number Formula

Mach Ratio = 1-Hypersonic Similarity Parameter*((Specific Heat Ratio-1)/2)
Ma = 1-K*((Y-1)/2)

What is a similarity parameter?

The hypersonic similarity is equivalent to the Van Dyke's similarity theory, that if the hypersonic similarity parameter K is fixed, the shock solution structures (after scaling) are consistent, when the Mach number of the flow is sufficiently large.

How to Calculate Mach Ratio at High Mach Number?

Mach Ratio at High Mach Number calculator uses Mach Ratio = 1-Hypersonic Similarity Parameter*((Specific Heat Ratio-1)/2) to calculate the Mach Ratio, The Mach ratio at high Mach number formula is defined as is the ratio between the Mach numbers before and after shock. Mach Ratio is denoted by Ma symbol.

How to calculate Mach Ratio at High Mach Number using this online calculator? To use this online calculator for Mach Ratio at High Mach Number, enter Hypersonic Similarity Parameter (K) & Specific Heat Ratio (Y) and hit the calculate button. Here is how the Mach Ratio at High Mach Number calculation can be explained with given input values -> 0.4 = 1-2*((1.6-1)/2).

FAQ

What is Mach Ratio at High Mach Number?

The Mach ratio at high Mach number formula is defined as is the ratio between the Mach numbers before and after shock and is represented as Ma = 1-K*((Y-1)/2) or Mach Ratio = 1-Hypersonic Similarity Parameter*((Specific Heat Ratio-1)/2). 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 & 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.

How to calculate Mach Ratio at High Mach Number?

The Mach ratio at high Mach number formula is defined as is the ratio between the Mach numbers before and after shock is calculated using Mach Ratio = 1-Hypersonic Similarity Parameter*((Specific Heat Ratio-1)/2). To calculate Mach Ratio at High Mach Number, you need Hypersonic Similarity Parameter (K) & Specific Heat Ratio (Y). With our tool, you need to enter the respective value for Hypersonic Similarity Parameter & Specific Heat Ratio 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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