Reynolds Number Equation using Local Mach Number Calculator

✖Boundary-layer momentum Reynolds number is the reynolds number at the transition region near the boundary layer.ⓘ Reynolds Number Equation using Local Mach Number [Re_θT]

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Formula

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Reynolds Number Equation using Local Mach Number

Formula

`"Re"_{"θT"} = 100*"M"_{"e"}`

Example

`"180"=100*"1.8"`

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Reynolds Number Equation using Local Mach Number Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

Variables Used

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

STEP 1: Convert Input(s) to Base Unit

Local Mach Number: 1.8 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

Re_θT = 100*M_e --> 100*1.8

Evaluating ... ...

Re_θT = 180

STEP 3: Convert Result to Output's Unit

180 --> No Conversion Required

FINAL ANSWER

180 <-- Boundary-layer Momentum Reynolds number

(Calculation completed in 00.005 seconds)

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Created by Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

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Verified by Vinay Mishra

Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune

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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

Reynolds Number Equation using Local Mach Number Formula

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

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 Reynolds Number Equation using Local Mach Number?

Reynolds Number Equation using Local Mach Number calculator uses Boundary-layer Momentum Reynolds number = 100*Local Mach Number to calculate the Boundary-layer Momentum Reynolds number, The Reynolds number equation using local Mach number formula is defined as the product of the constant and local Mach at the transition region. Boundary-layer Momentum Reynolds number is denoted by Re_θT symbol.

How to calculate Reynolds Number Equation using Local Mach Number using this online calculator? To use this online calculator for Reynolds Number Equation using Local Mach Number, enter Local Mach Number (M_e) and hit the calculate button. Here is how the Reynolds Number Equation using Local Mach Number calculation can be explained with given input values -> 180 = 100*1.8.

FAQ

What is Reynolds Number Equation using Local Mach Number?

The Reynolds number equation using local Mach number formula is defined as the product of the constant and local Mach at the transition region and is represented as Re_θT = 100*M_e or Boundary-layer Momentum Reynolds number = 100*Local Mach Number. Local Mach Number is the ratio of the free-stream flow to the local speed of sound.

How to calculate Reynolds Number Equation using Local Mach Number?

The Reynolds number equation using local Mach number formula is defined as the product of the constant and local Mach at the transition region is calculated using Boundary-layer Momentum Reynolds number = 100*Local Mach Number. To calculate Reynolds Number Equation using Local Mach Number, you need Local Mach Number (M_e). With our tool, you need to enter the respective value for Local Mach 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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