Perpendicular Upstream Flow Components behind Shock Wave Solution

STEP 0: Pre-Calculation Summary
Formula Used
Perpendicular upstream flow components = (Velocity of the fluid at 1*(sin(2*Wave Angle)))/(Specific Heat Ratio-1)
v2 = (V1*(sin(2*β)))/(Y-1)
This formula uses 1 Functions, 4 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
Perpendicular upstream flow components - (Measured in Meter per Second) - Perpendicular upstream flow components of the flow velocity behind the shock wave perpendicular to the upstream flow.
Velocity of the fluid at 1 - (Measured in Meter per Second) - Velocity of the fluid at 1 is defined as the velocity of the flowing liquid at a point 1.
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
Velocity of the fluid at 1: 26.2 Meter per Second --> 26.2 Meter per Second No Conversion Required
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
v2 = (V1*(sin(2*β)))/(Y-1) --> (26.2*(sin(2*0.286)))/(1.6-1)
Evaluating ... ...
v2 = 23.6374116363469
STEP 3: Convert Result to Output's Unit
23.6374116363469 Meter per Second --> No Conversion Required
FINAL ANSWER
23.6374116363469 23.63741 Meter per Second <-- Perpendicular upstream flow components
(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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15 Oblique Shock Relation Calculators

Exact Density Ratio
Go Density Ratio = ((Specific Heat Ratio+1)*(Mach Number*(sin(Wave Angle)))^2)/((Specific Heat Ratio-1)*(Mach Number*(sin(Wave Angle)))^2+2)
Temperature Ratio when Mach Becomes Infinite
Go Temperature Ratio = (2*Specific Heat Ratio*(Specific Heat Ratio-1))/(Specific Heat Ratio+1)^2*(Mach Number*sin(Wave Angle))^2
Exact Pressure Ratio
Go Pressure Ratio = 1+2*Specific Heat Ratio/(Specific Heat Ratio+1)*((Mach Number*sin(Wave Angle))^2-1)
Pressure Ratio when Mach becomes Infinite
Go Pressure Ratio = (2*Specific Heat Ratio)/(Specific Heat Ratio+1)*(Mach Number*sin(Wave Angle))^2
Parallel Upstream Flow Components after Shock as Mach Tends to Infinite
Go Parallel upstream flow components = Velocity of the fluid at 1*(1-(2*(sin(Wave Angle))^2)/(Specific Heat Ratio-1))
Perpendicular Upstream Flow Components behind Shock Wave
Go Perpendicular upstream flow components = (Velocity of the fluid at 1*(sin(2*Wave Angle)))/(Specific Heat Ratio-1)
Pressure Coefficient behind Oblique Shock Wave
Go Pressure Coefficient = 4/(Specific Heat Ratio+1)*((sin(Wave Angle))^2-1/Mach Number^2)
Wave Angle for Small Deflection Angle
Go Wave Angle = (Specific Heat Ratio+1)/2*(Deflection Angle*180/pi)*pi/180
Velocity of Sound using Dynamic Pressure and Density
Go Speed of Sound = sqrt((Specific Heat Ratio*Pressure)/Density)
Dynamic Pressure for given Specific Heat Ratio and Mach Number
Go Dynamic Pressure = Specific Heat Ratio Dynamic*Static Pressure*(Mach Number^2)/2
Pressure Coefficient behind Oblique Shock Wave for Infinite Mach Number
Go Pressure Coefficient = 4/(Specific Heat Ratio+1)*(sin(Wave Angle))^2
Non-Dimensional Pressure Coefficient
Go Pressure Coefficient = Change in static pressure/Dynamic Pressure
Density Ratio when Mach Becomes Infinite
Go Density Ratio = (Specific Heat Ratio+1)/(Specific Heat Ratio-1)
Temperature Ratios
Go Temperature Ratio = Pressure Ratio/Density Ratio
Coefficient of Pressure Derived from Oblique Shock Theory
Go Pressure Coefficient = 2*(sin(Wave Angle))^2

Perpendicular Upstream Flow Components behind Shock Wave Formula

Perpendicular upstream flow components = (Velocity of the fluid at 1*(sin(2*Wave Angle)))/(Specific Heat Ratio-1)
v2 = (V1*(sin(2*β)))/(Y-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 Perpendicular Upstream Flow Components behind Shock Wave?

Perpendicular Upstream Flow Components behind Shock Wave calculator uses Perpendicular upstream flow components = (Velocity of the fluid at 1*(sin(2*Wave Angle)))/(Specific Heat Ratio-1) to calculate the Perpendicular upstream flow components, The Perpendicular upstream flow components behind shock wave formula is defined as perpendicular component of the flow velocity after oblique shock occurs and Mach is infinite. Perpendicular upstream flow components is denoted by v2 symbol.

How to calculate Perpendicular Upstream Flow Components behind Shock Wave using this online calculator? To use this online calculator for Perpendicular Upstream Flow Components behind Shock Wave, enter Velocity of the fluid at 1 (V1), Wave Angle (β) & Specific Heat Ratio (Y) and hit the calculate button. Here is how the Perpendicular Upstream Flow Components behind Shock Wave calculation can be explained with given input values -> 23.65459 = (26.2*(sin(2*0.286)))/(1.6-1).

FAQ

What is Perpendicular Upstream Flow Components behind Shock Wave?
The Perpendicular upstream flow components behind shock wave formula is defined as perpendicular component of the flow velocity after oblique shock occurs and Mach is infinite and is represented as v2 = (V1*(sin(2*β)))/(Y-1) or Perpendicular upstream flow components = (Velocity of the fluid at 1*(sin(2*Wave Angle)))/(Specific Heat Ratio-1). Velocity of the fluid at 1 is defined as the velocity of the flowing liquid at a point 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 Perpendicular Upstream Flow Components behind Shock Wave?
The Perpendicular upstream flow components behind shock wave formula is defined as perpendicular component of the flow velocity after oblique shock occurs and Mach is infinite is calculated using Perpendicular upstream flow components = (Velocity of the fluid at 1*(sin(2*Wave Angle)))/(Specific Heat Ratio-1). To calculate Perpendicular Upstream Flow Components behind Shock Wave, you need Velocity of the fluid at 1 (V1), Wave Angle (β) & Specific Heat Ratio (Y). With our tool, you need to enter the respective value for Velocity of the fluid at 1, 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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