Non-Dimensional Parallel Velocity Component for High Mach Number Solution

STEP 0: Pre-Calculation Summary
Formula Used
Non Dimensionalized Upstream Parallel Velocity = 1-(2*(sin(Wave Angle))^2)/(Specific Heat Ratio-1)
u- = 1-(2*(sin(β))^2)/(γ-1)
This formula uses 1 Functions, 3 Variables
Functions Used
sin - Sine is a trigonometric function that describes the ratio of the length of the opposite side of a right triangle to the length of the hypotenuse., sin(Angle)
Variables Used
Non Dimensionalized Upstream Parallel Velocity - The Non Dimensionalized Upstream Parallel Velocity is the non dimensional form of the components of the flow velocity behind the shock wave parallel to the upstream flow.
Wave Angle - (Measured in Radian) - Wave Angle is the shock angle created by the oblique shock, this is not similar to the mach angle.
Specific Heat Ratio - The Specific heat ratio of a gas is the ratio of the specific heat of the gas at a constant pressure to its specific heat at a constant volume.
STEP 1: Convert Input(s) to Base Unit
Wave Angle: 0.286 Radian --> 0.286 Radian No Conversion Required
Specific Heat Ratio: 1.6 --> No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
u- = 1-(2*(sin(β))^2)/(γ-1) --> 1-(2*(sin(0.286))^2)/(1.6-1)
Evaluating ... ...
u- = 0.734700046638202
STEP 3: Convert Result to Output's Unit
0.734700046638202 --> No Conversion Required
FINAL ANSWER
0.734700046638202 0.7347 <-- Non Dimensionalized Upstream Parallel Velocity
(Calculation completed in 00.004 seconds)

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Created by Sanjay Krishna
Amrita School of Engineering (ASE), Vallikavu
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11 Approximate Methods of Hypersonic Inviscid Flowfields Calculators

Non-Dimensional Parallel Velocity Component for High Mach Number
Go Non Dimensionalized Upstream Parallel Velocity = 1-(2*(sin(Wave Angle))^2)/(Specific Heat Ratio-1)
Transformed Conical Variable
Go Transformed Conical Variable = Radius of Cone/(Slenderness Ratio*Height of Cone)
Non-Dimensional Radius for Hypersonic Vehicles
Go Non Dimensionalized Radius = Radius of Cone/(Slenderness Ratio*Height of Cone)
Non-Dimensional Pressure for High Mach Number
Go Non Dimensionalized Pressure = (2*(sin(Wave Angle)^2))/(Specific Heat Ratio+1)
Non-Dimensional Perpendicular Velocity Component for High Mach Number
Go Non Dimensionalized Velocity = (sin(2*Wave Angle))/(Specific Heat Ratio-1)
Transformed Conical Variable with Cone Angle in Hypersonic Flow
Go Transformed Conical Variable = (Wave Angle*(180/pi))/Semi Angle of Cone
Transformed Conical Variable with Wave Angle
Go Transformed Conical Variable = (Wave Angle*(180/pi))/Slenderness Ratio
Non-Dimensional Pressure
Go Non Dimensionalized Pressure = Pressure/(Density*Freestream Velocity^2)
Non-Dimensional Density for High Mach Number
Go Non Dimensionalized Density = (Specific Heat Ratio+1)/(Specific Heat Ratio-1)
Non-Dimensional Density
Go Non Dimensionalized Density = Density/Liquid Density
Slenderness Ratio with Cone Radius for Hypersonic Vehicle
Go Slenderness Ratio = Radius of Cone/Height of Cone

Non-Dimensional Parallel Velocity Component for High Mach Number Formula

Non Dimensionalized Upstream Parallel Velocity = 1-(2*(sin(Wave Angle))^2)/(Specific Heat Ratio-1)
u- = 1-(2*(sin(β))^2)/(γ-1)

What is velocity component?

The two parts of a vector are known as components and describe the influence of that vector in a single direction. If a projectile is launched at an angle to the horizontal, then the initial velocity of the projectile has both a horizontal and a vertical component.

How to Calculate Non-Dimensional Parallel Velocity Component for High Mach Number?

Non-Dimensional Parallel Velocity Component for High Mach Number calculator uses Non Dimensionalized Upstream Parallel Velocity = 1-(2*(sin(Wave Angle))^2)/(Specific Heat Ratio-1) to calculate the Non Dimensionalized Upstream Parallel Velocity, The Non-dimensional parallel velocity component for high mach number formula is defined as the parallel component of the flow velocity after oblique shock occurs and Mach is infinite. Non Dimensionalized Upstream Parallel Velocity is denoted by u- symbol.

How to calculate Non-Dimensional Parallel Velocity Component for High Mach Number using this online calculator? To use this online calculator for Non-Dimensional Parallel Velocity Component for High Mach Number, enter Wave Angle (β) & Specific Heat Ratio (γ) and hit the calculate button. Here is how the Non-Dimensional Parallel Velocity Component for High Mach Number calculation can be explained with given input values -> 0.734278 = 1-(2*(sin(0.286))^2)/(1.6-1).

FAQ

What is Non-Dimensional Parallel Velocity Component for High Mach Number?
The Non-dimensional parallel velocity component for high mach number formula is defined as the parallel component of the flow velocity after oblique shock occurs and Mach is infinite and is represented as u- = 1-(2*(sin(β))^2)/(γ-1) or Non Dimensionalized Upstream Parallel Velocity = 1-(2*(sin(Wave Angle))^2)/(Specific Heat Ratio-1). Wave Angle is the shock angle created by the oblique shock, this is not similar to the mach angle & The Specific heat ratio of a gas is the ratio of the specific heat of the gas at a constant pressure to its specific heat at a constant volume.
How to calculate Non-Dimensional Parallel Velocity Component for High Mach Number?
The Non-dimensional parallel velocity component for high mach number formula is defined as the parallel component of the flow velocity after oblique shock occurs and Mach is infinite is calculated using Non Dimensionalized Upstream Parallel Velocity = 1-(2*(sin(Wave Angle))^2)/(Specific Heat Ratio-1). To calculate Non-Dimensional Parallel Velocity Component for High Mach Number, you need Wave Angle (β) & Specific Heat Ratio (γ). With our tool, you need to enter the respective value for Wave Angle & Specific Heat Ratio 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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