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' = vfluid-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' = vfluid-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)

Credits

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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12 Hypersonic Small Disturbance Equations 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)
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)
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
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' = vfluid-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 (vfluid) & 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' = vfluid-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 (vfluid) & 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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