Local Mach Number using Reynolds Number Equation at Transition Region Calculator

✖Boundary-layer momentum Reynolds number is the reynolds number at the transition region near the boundary layer.ⓘ Boundary-layer Momentum Reynolds number [Re_θT]

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✖Local Mach Number is the ratio of the free-stream flow to the local speed of sound.ⓘ Local Mach Number using Reynolds Number Equation at Transition Region [M_e]

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Formula

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Local Mach Number using Reynolds Number Equation at Transition Region

Formula

`"M"_{"e"} = "Re"_{"θT"}/100`

Example

`"20"="2000"/100`

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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 - Local Mach Number is the ratio of the free-stream flow to the local speed of sound.
Boundary-layer Momentum Reynolds number - Boundary-layer momentum Reynolds number is the reynolds number at the transition region near the boundary layer.

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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< 16 Hypersonic Transition Calculators

Boundary-Layer Momentum Thickness using Reynolds Number at Transition Point

Go Boundary-layer momentum thickness for transition = (Reynolds Number*Static Viscosity)/(Static Velocity*Static Density)

Static Density Equation using Boundary-Layer Momentum Thickness

Go Static Density = (Reynolds Number*Static Viscosity)/(Static Velocity*Boundary-layer momentum thickness for transition)

Static Velocity using Boundary-Layer Momentum Thickness

Go Static Velocity = (Reynolds Number*Static Viscosity)/(Static Density*Boundary-layer momentum thickness for transition)

Static Viscosity Equation using Boundary-Layer Momentum Thickness

Go Static Viscosity = (Static Density*Static Velocity*Boundary-layer momentum thickness for transition)/Reynolds Number

Reynolds Number Equation using Boundary-Layer Momentum Thickness

Go Reynolds Number = (Static Density*Static Velocity*Boundary-layer momentum thickness for transition)/Static Viscosity

Static Velocity at Transition Point

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

Static Density at Transition Point

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

Location of Transition Point

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

Static Viscosity at Transition Point

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

Transition Reynolds Number

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

Specific Heat at Constant Pressure for Transient Flow

Go Molar Specific Heat Capacity at Constant Pressure = (Transient Prandtl Number*Transition Thermal Conductivity)/Eddy Viscosity

Prandtl Number of Transition Flow

Go Transient Prandtl Number = (Eddy Viscosity*Molar Specific Heat Capacity at Constant Pressure)/Transition Thermal Conductivity

Eddy Viscosity Calculation

Go Eddy Viscosity = (Transition Thermal Conductivity*Transient Prandtl Number)/Molar Specific Heat Capacity at Constant Pressure

Thermal Conductivity of Transition Flow

Go Transition Thermal Conductivity = (Eddy Viscosity*Specific Heat Capacity)/Transient Prandtl Number

Local Mach Number using Reynolds Number Equation at Transition Region

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

Reynolds Number Equation using Local Mach Number

Go Boundary-layer Momentum Reynolds number = 100*Local Mach Number

Local Mach Number using Reynolds Number Equation at Transition Region Formula

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, The Local Mach Number using Reynolds number equation at transition region formula is defined as the ratio of Reynolds number at the boundary layer during transition region by a constant. 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?

The Local Mach Number using Reynolds number equation at transition region formula is defined as the ratio of Reynolds number at the boundary layer during transition region by a constant and is represented as M_e = Re_θT/100 or Local Mach Number = Boundary-layer Momentum Reynolds number/100. Boundary-layer momentum Reynolds number is the reynolds number at the transition region near the boundary layer.

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

The Local Mach Number using Reynolds number equation at transition region formula is defined as the ratio of Reynolds number at the boundary layer during transition region by a constant 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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