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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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

Sanjay Krishna has created this Calculator and 300+ more calculators!

Verified by Maiarutselvan V

PSG College of Technology (PSGCT), Coimbatore

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< Hypersonic Flow Parameters Calculators

Coefficient of Pressure with Similarity Parameters

LaTeX 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))

Deflection Angle

LaTeX Go Deflection Angle = 2/(Specific Heat Ratio-1)*(1/Mach Number ahead of Shock-1/Mach Number Behind Shock)

Coefficient of Drag

LaTeX Go Drag Coefficient = Drag Force/(Dynamic Pressure*Area For Flow)

Axial Force Coefficient

LaTeX Go Coefficient of Force = Force/(Dynamic Pressure*Area For Flow)

Mach Ratio at High Mach Number Formula

LaTeX Go

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, Mach Ratio at High Mach Number formula is defined as a dimensionless quantity used to describe the speed of an object moving at hypersonic velocities, typically above Mach 5, where the flow characteristics change significantly, and it plays a crucial role in the study of hypersonic flow parameters. 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?

Mach Ratio at High Mach Number formula is defined as a dimensionless quantity used to describe the speed of an object moving at hypersonic velocities, typically above Mach 5, where the flow characteristics change significantly, and it plays a crucial role in the study of hypersonic flow parameters 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?

Mach Ratio at High Mach Number formula is defined as a dimensionless quantity used to describe the speed of an object moving at hypersonic velocities, typically above Mach 5, where the flow characteristics change significantly, and it plays a crucial role in the study of hypersonic flow parameters 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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