Change in Velocity for Hypersonic Flow in X Direction Calculator

✖Fluid Velocity is the volume of fluid flowing in the given vessel per unit cross sectional area.ⓘ Fluid Velocity [v_fluid]			+10% -10%
✖Freestream Velocity Normal is the velocity of air far upstream of an aerodynamic body, that is before the body has a chance to deflect, slow down or compress the air.ⓘ Freestream Velocity Normal [U_∞]			+10% -10%

✖Change in velocity for Hypersonic Flow states that the total flow velocity is free stream velocity plus change in velocity.ⓘ Change in Velocity for Hypersonic Flow in X Direction [u']

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Formula

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Change in Velocity for Hypersonic Flow in X Direction

Formula

`"u'" = "v"_{"fluid"}-"U"_{"∞"}`

Example

`"3.2m/s"="105.2m/s"-"102m/s"`

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Change in Velocity for Hypersonic Flow in X Direction Solution

STEP 0: Pre-Calculation Summary

Formula Used

Change in Velocity for Hypersonic Flow = Fluid Velocity-Freestream Velocity Normal
u' = v_fluid-U_∞
This formula uses 3 Variables

Variables Used

Change in Velocity for Hypersonic Flow - (Measured in Meter per Second) - Change in velocity for Hypersonic Flow states that the total flow velocity is free stream velocity plus change in velocity.
Fluid Velocity - (Measured in Meter per Second) - Fluid Velocity is the volume of fluid flowing in the given vessel per unit cross sectional area.
Freestream Velocity Normal - (Measured in Meter per Second) - Freestream Velocity Normal is the velocity of air far upstream of an aerodynamic body, that is before the body has a chance to deflect, slow down or compress the air.

STEP 1: Convert Input(s) to Base Unit

Fluid Velocity: 105.2 Meter per Second --> 105.2 Meter per Second No Conversion Required
Freestream Velocity Normal: 102 Meter per Second --> 102 Meter per Second No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

u' = v_fluid-U_∞ --> 105.2-102

Evaluating ... ...

u' = 3.2

STEP 3: Convert Result to Output's Unit

3.2 Meter per Second --> No Conversion Required

FINAL ANSWER

3.2 Meter per Second <-- Change in Velocity for Hypersonic Flow

(Calculation completed in 00.004 seconds)

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Created by Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

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Verified by Maiarutselvan V

PSG College of Technology (PSGCT), Coimbatore

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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)

Change in Velocity for Hypersonic Flow in X Direction Formula

Change in Velocity for Hypersonic Flow = Fluid Velocity-Freestream Velocity Normal
u' = v_fluid-U_∞

What is hypersonic flow?

Hypersonic flows are flow fields where the fluid velocity is much larger than the velocity of propagation of small disturbances, the velocity of sound.

How to Calculate Change in Velocity for Hypersonic Flow in X Direction?

Change in Velocity for Hypersonic Flow in X Direction calculator uses Change in Velocity for Hypersonic Flow = Fluid Velocity-Freestream Velocity Normal to calculate the Change in Velocity for Hypersonic Flow, Change in velocity for hypersonic flow in x direction formula is defined as the velocity of fluid in x direction after the impact of body minus the free stream velocity. Change in Velocity for Hypersonic Flow is denoted by u' symbol.

How to calculate Change in Velocity for Hypersonic Flow in X Direction using this online calculator? To use this online calculator for Change in Velocity for Hypersonic Flow in X Direction, enter Fluid Velocity (v_fluid) & Freestream Velocity Normal (U_∞) and hit the calculate button. Here is how the Change in Velocity for Hypersonic Flow in X Direction calculation can be explained with given input values -> 3.2 = 105.2-102.

FAQ

What is Change in Velocity for Hypersonic Flow in X Direction?

Change in velocity for hypersonic flow in x direction formula is defined as the velocity of fluid in x direction after the impact of body minus the free stream velocity and is represented as u' = v_fluid-U_∞ or Change in Velocity for Hypersonic Flow = Fluid Velocity-Freestream Velocity Normal. Fluid Velocity is the volume of fluid flowing in the given vessel per unit cross sectional area & Freestream Velocity Normal is the velocity of air far upstream of an aerodynamic body, that is before the body has a chance to deflect, slow down or compress the air.

How to calculate Change in Velocity for Hypersonic Flow in X Direction?

Change in velocity for hypersonic flow in x direction formula is defined as the velocity of fluid in x direction after the impact of body minus the free stream velocity is calculated using Change in Velocity for Hypersonic Flow = Fluid Velocity-Freestream Velocity Normal. To calculate Change in Velocity for Hypersonic Flow in X Direction, you need Fluid Velocity (v_fluid) & Freestream Velocity Normal (U_∞). With our tool, you need to enter the respective value for Fluid Velocity & Freestream Velocity Normal 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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