Inverse of Density for Hypersonic Flow Calculator

✖The Density of a material shows the denseness of that material in a specific given area. This is taken as mass per unit volume of a given object.ⓘ Density [ρ]			+10% -10%
✖Wave Angle is the shock angle created by the oblique shock, this is not similar to the mach angle.ⓘ Wave Angle [β]			+10% -10%

✖Inverse of Density is the variable used for simplifying the equation.ⓘ Inverse of Density for Hypersonic Flow [ϵ]

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Formula

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Inverse of Density for Hypersonic Flow

Formula

`"ϵ" = 1/("ρ"*"β")`

Example

`"0.003507m³/kg"=1/("997kg/m³"*"0.286rad")`

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Inverse of Density for Hypersonic Flow Solution

STEP 0: Pre-Calculation Summary

Formula Used

Inverse of Density = 1/(Density*Wave Angle)
ϵ = 1/(ρ*β)
This formula uses 3 Variables

Variables Used

Inverse of Density - (Measured in Cubic Meter per Kilogram) - Inverse of Density is the variable used for simplifying the equation.
Density - (Measured in Kilogram per Cubic Meter) - The Density of a material shows the denseness of that material in a specific given area. This is taken as mass per unit volume of a given object.
Wave Angle - (Measured in Radian) - Wave Angle is the shock angle created by the oblique shock, this is not similar to the mach angle.

STEP 1: Convert Input(s) to Base Unit

Density: 997 Kilogram per Cubic Meter --> 997 Kilogram per Cubic Meter No Conversion Required
Wave Angle: 0.286 Radian --> 0.286 Radian No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

ϵ = 1/(ρ*β) --> 1/(997*0.286)

Evaluating ... ...

ϵ = 0.00350702457021414

STEP 3: Convert Result to Output's Unit

0.00350702457021414 Cubic Meter per Kilogram --> No Conversion Required

FINAL ANSWER

0.00350702457021414 ≈ 0.003507 Cubic Meter per Kilogram <-- Inverse of Density

(Calculation completed in 00.004 seconds)

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Created by Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

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K J Somaiya College of Engineering (K J Somaiya), Mumbai

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< 17 Hypersonic Flow and Disturbances Calculators

Inverse of Density for Hypersonic Flow using Mach Number

Go Inverse of Density = (2+(Specific Heat Ratio-1)*Mach Number^2*sin(Deflection Angle)^2)/(2+(Specific Heat Ratio+1)*Mach Number^2*sin(Deflection Angle)^2)

Coefficient of Pressure with Slenderness Ratio and Similarity Constant

Go Pressure Coefficient = (2*Slenderness Ratio^2)/(Specific Heat Ratio*Hypersonic Similarity Parameter^2)*(Specific Heat Ratio*Hypersonic Similarity Parameter^2*Non Dimensionalized Pressure-1)

Coefficient of Pressure with Slenderness Ratio

Go Pressure Coefficient = 2/Specific Heat Ratio*Mach Number^2*(Non Dimensionalized Pressure*Specific Heat Ratio*Mach Number^2*Slenderness Ratio^2-1)

Non Dimensional Pressure Equation with Slenderness Ratio

Go Non Dimensionalized Pressure = Pressure/(Specific Heat Ratio*Mach Number^2*Slenderness Ratio^2*Free Stream Pressure)

Density Ratio with Similarity Constant having Slenderness Ratio

Go Density Ratio = ((Specific Heat Ratio+1)/(Specific Heat Ratio-1))*(1/(1+2/((Specific Heat Ratio-1)*Hypersonic Similarity Parameter^2)))

Rasmussen Closed Form Expression for Shock Wave Angle

Go Wave Angle Similarity Parameter = Hypersonic Similarity Parameter*sqrt((Specific Heat Ratio+1)/2+1/Hypersonic Similarity Parameter^2)

Non Dimensional Change in Hypersonic Disturbance Velocity in y Direction

Go Non Dimensional Disturbance Y Velocity = Change in Velocity for Hypersonic Flow y direction/(Freestream Velocity Normal*Slenderness Ratio)

Non Dimensional Change in Hypersonic Disturbance Velocity in x Direction

Go Non Dimensional Disturbance X Velocity = Change in Velocity for Hypersonic Flow/(Freestream Velocity for Blast Wave*Slenderness Ratio^2)

Doty and Rasmussen- Normal Force Coefficient

Go Coefficient of Force = 2*Normal Force/(Density of Fluid*Freestream Velocity Normal^2*Area)

Constant G used for Finding Location of Perturbed Shock

Go Perturbed Shock Location Constant = Perturbed Shock Location Constant at Normal Force/Perturbed Shock Location Constant at Drag Force

Non Dimensional Velocity Disturbance in y Direction in Hypersonic Flow

Go Non Dimensional Disturbance Y Velocity = (2/(Specific Heat Ratio+1))*(1-1/Hypersonic Similarity Parameter^2)

Non Dimensionalised Time

Go Non Dimensionalized Time = Time/(Length/Freestream Velocity Normal)

Similarity Constant Equation using Wave Angle

Go Wave Angle Similarity Parameter = Mach Number*Wave Angle*180/pi

Change in Velocity for Hypersonic Flow in X Direction

Go Change in Velocity for Hypersonic Flow = Fluid Velocity-Freestream Velocity Normal

Distance from Tip of Leading Edge to Base

Go Distance from X-Axis = Freestream Velocity for Blast Wave*Total Time Taken

Similarity Constant Equation with Slenderness Ratio

Go Hypersonic Similarity Parameter = Mach Number*Slenderness Ratio

Inverse of Density for Hypersonic Flow

Go Inverse of Density = 1/(Density*Wave Angle)

Inverse of Density for Hypersonic Flow Formula

Inverse of Density = 1/(Density*Wave Angle)
ϵ = 1/(ρ*β)

What is a shock?

Shock wave, strong pressure wave in any elastic medium such as air, water, or a solid substance, produced by supersonic aircraft, explosions, lightning, or other phenomena that create violent changes in pressure

How to Calculate Inverse of Density for Hypersonic Flow?

Inverse of Density for Hypersonic Flow calculator uses Inverse of Density = 1/(Density*Wave Angle) to calculate the Inverse of Density, The Inverse of density for hypersonic flow formula is defined as the inverse of product of the density of the flow and wave angle created by shock. Inverse of Density is denoted by ϵ symbol.

How to calculate Inverse of Density for Hypersonic Flow using this online calculator? To use this online calculator for Inverse of Density for Hypersonic Flow, enter Density (ρ) & Wave Angle (β) and hit the calculate button. Here is how the Inverse of Density for Hypersonic Flow calculation can be explained with given input values -> 0.003507 = 1/(997*0.286).

FAQ

What is Inverse of Density for Hypersonic Flow?

The Inverse of density for hypersonic flow formula is defined as the inverse of product of the density of the flow and wave angle created by shock and is represented as ϵ = 1/(ρ*β) or Inverse of Density = 1/(Density*Wave Angle). The Density of a material shows the denseness of that material in a specific given area. This is taken as mass per unit volume of a given object & Wave Angle is the shock angle created by the oblique shock, this is not similar to the mach angle.

How to calculate Inverse of Density for Hypersonic Flow?

The Inverse of density for hypersonic flow formula is defined as the inverse of product of the density of the flow and wave angle created by shock is calculated using Inverse of Density = 1/(Density*Wave Angle). To calculate Inverse of Density for Hypersonic Flow, you need Density (ρ) & Wave Angle (β). With our tool, you need to enter the respective value for Density & Wave Angle and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

How many ways are there to calculate Inverse of Density?

In this formula, Inverse of Density uses Density & Wave Angle. We can use 1 other way(s) to calculate the same, which is/are as follows -

Inverse of Density = (2+(Specific Heat Ratio-1)*Mach Number^2*sin(Deflection Angle)^2)/(2+(Specific Heat Ratio+1)*Mach Number^2*sin(Deflection Angle)^2)

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