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Local Mach Number using Reynolds Number Equation at Transition Region Formula

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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. Check FAQs

M e = \frac{Re θT}{100}

M_e - Local Mach Number?Re_θT - Boundary-layer Momentum Reynolds number?

Local Mach Number using Reynolds Number Equation at Transition Region Example

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Here is how the Local Mach Number using Reynolds Number Equation at Transition Region equation looks like with Values.

Here is how the Local Mach Number using Reynolds Number Equation at Transition Region equation looks like with Units.

Here is how the Local Mach Number using Reynolds Number Equation at Transition Region equation looks like.

20 = \frac{2000}{100}

20 = \frac{2000}{100}

20 = \frac{2000}{100}

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Local Mach Number using Reynolds Number Equation at Transition Region Solution

Follow our step by step solution on how to calculate Local Mach Number using Reynolds Number Equation at Transition Region?

FIRST Step Consider the formula

M e = \frac{Re θT}{100}

Next Step Substitute values of Variables

∴

M e = \frac{2000}{100}

Next Step Prepare to Evaluate

∴

M e = \frac{2000}{100}

LAST Step Evaluate

∴

M e = 20

Local Mach Number using Reynolds Number Equation at Transition Region Formula Elements

Variables

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.

Symbol: M_e

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Local Mach Number

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.

Symbol: Re_θT

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Boundary-layer Momentum Reynolds number

Other formulas in Hypersonic Transition category

Go Transition Reynolds Number

Ret = \frac{ρ e \cdot u e \cdot xt}{μe}

Go Static Density at Transition Point

ρ e = \frac{Ret \cdot μe}{u e \cdot xt}

Go Static Velocity at Transition Point

u e = \frac{Ret \cdot μe}{ρ e \cdot xt}

Go Location of Transition Point

xt = \frac{Ret \cdot μe}{u e \cdot ρ e}

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

Local Mach Number using Reynolds Number Equation at Transition Region evaluator uses Local Mach Number = Boundary-layer Momentum Reynolds number/100 to evaluate 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 evaluate Local Mach Number using Reynolds Number Equation at Transition Region using this online evaluator? To use this online evaluator for Local Mach Number using Reynolds Number Equation at Transition Region, enter Boundary-layer Momentum Reynolds number (Re_θT) and hit the calculate button.

FAQs on Local Mach Number using Reynolds Number Equation at Transition Region

What is the formula to find Local Mach Number using Reynolds Number Equation at Transition Region?

The formula of Local Mach Number using Reynolds Number Equation at Transition Region is expressed as Local Mach Number = Boundary-layer Momentum Reynolds number/100. Here is an example- 20 = 2000/100.

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

With Boundary-layer Momentum Reynolds number (Re_θT) we can find Local Mach Number using Reynolds Number Equation at Transition Region using the formula - Local Mach Number = Boundary-layer Momentum Reynolds number/100.

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