Local Mach Number using Reynolds Number Equation at Transition Region Calculator

✖The Boundary-layer Momentum Reynolds number is a dimensionless quantity that characterizes the flow regime in a boundary layer, indicating the relative importance of inertial forces to viscous forces.ⓘ Boundary-layer Momentum Reynolds number [Re_θT]

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✖The Local Mach Number is the ratio of the local flow velocity to the speed of sound in the medium, indicating the flow regime around an object.ⓘ Local Mach Number using Reynolds Number Equation at Transition Region [M_e]

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Local Mach Number using Reynolds Number Equation at Transition Region Solution

STEP 0: Pre-Calculation Summary

Formula Used

Local Mach Number = Boundary-layer Momentum Reynolds number/100
M_e = Re_θT/100
This formula uses 2 Variables

Variables Used

Local Mach Number - The Local Mach Number is the ratio of the local flow velocity to the speed of sound in the medium, indicating the flow regime around an object.
Boundary-layer Momentum Reynolds number - The Boundary-layer Momentum Reynolds number is a dimensionless quantity that characterizes the flow regime in a boundary layer, indicating the relative importance of inertial forces to viscous forces.

STEP 1: Convert Input(s) to Base Unit

Boundary-layer Momentum Reynolds number: 2000 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

M_e = Re_θT/100 --> 2000/100

Evaluating ... ...

M_e = 20

STEP 3: Convert Result to Output's Unit

20 --> No Conversion Required

FINAL ANSWER

20 <-- Local Mach Number

(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 Transition Calculators

Static Velocity at Transition Point

LaTeX Go Static Velocity = (Transition Reynolds Number*Static Viscosity)/(Static Density*Location Transition Point)

Static Density at Transition Point

LaTeX Go Static Density = (Transition Reynolds Number*Static Viscosity)/(Static Velocity*Location Transition Point)

Location of Transition Point

LaTeX Go Location Transition Point = (Transition Reynolds Number*Static Viscosity)/(Static Velocity*Static Density)

Transition Reynolds Number

LaTeX Go Transition Reynolds Number = (Static Density*Static Velocity*Location Transition Point)/Static Viscosity

Local Mach Number using Reynolds Number Equation at Transition Region Formula

LaTeX Go

Local Mach Number = Boundary-layer Momentum Reynolds number/100
M_e = Re_θT/100

What is Local Mach?

The ratio of the free-stream flow to the local speed of sound. The speed of sound varies because of temperature changes around the aircraft, and thus the local Mach number may be more, less, or equal to the free-stream Mach number.

How to Calculate Local Mach Number using Reynolds Number Equation at Transition Region?

Local Mach Number using Reynolds Number Equation at Transition Region calculator uses Local Mach Number = Boundary-layer Momentum Reynolds number/100 to calculate the Local Mach Number, Local Mach Number using Reynolds Number Equation at Transition Region formula is defined as a dimensionless quantity that characterizes the compressibility of fluid flow in the transition region of a flat plate, providing a critical value for the onset of turbulence in viscous flow cases. Local Mach Number is denoted by M_e symbol.

How to calculate Local Mach Number using Reynolds Number Equation at Transition Region using this online calculator? To use this online calculator for Local Mach Number using Reynolds Number Equation at Transition Region, enter Boundary-layer Momentum Reynolds number (Re_θT) and hit the calculate button. Here is how the Local Mach Number using Reynolds Number Equation at Transition Region calculation can be explained with given input values -> 20 = 2000/100.

FAQ

What is Local Mach Number using Reynolds Number Equation at Transition Region?

Local Mach Number using Reynolds Number Equation at Transition Region formula is defined as a dimensionless quantity that characterizes the compressibility of fluid flow in the transition region of a flat plate, providing a critical value for the onset of turbulence in viscous flow cases and is represented as M_e = Re_θT/100 or Local Mach Number = Boundary-layer Momentum Reynolds number/100. The Boundary-layer Momentum Reynolds number is a dimensionless quantity that characterizes the flow regime in a boundary layer, indicating the relative importance of inertial forces to viscous forces.

How to calculate Local Mach Number using Reynolds Number Equation at Transition Region?

Local Mach Number using Reynolds Number Equation at Transition Region formula is defined as a dimensionless quantity that characterizes the compressibility of fluid flow in the transition region of a flat plate, providing a critical value for the onset of turbulence in viscous flow cases is calculated using Local Mach Number = Boundary-layer Momentum Reynolds number/100. To calculate Local Mach Number using Reynolds Number Equation at Transition Region, you need Boundary-layer Momentum Reynolds number (Re_θT). With our tool, you need to enter the respective value for Boundary-layer Momentum Reynolds number 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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