Parallel Upstream Flow Components after Shock as Mach Tends to Infinite Calculator

✖The Velocity of the fluid at 1 is the speed of the fluid at a specific point in a flow system, crucial for analyzing fluid behavior in various applications.ⓘ Velocity of the fluid at 1 [V₁]			+10% -10%
✖The Wave Angle is the angle between the direction of a hypersonic flow and the wave generated by an oblique shock in fluid mechanics.ⓘ Wave Angle [β]			+10% -10%
✖The Specific Heat Ratio is the ratio of the heat capacity at constant pressure to the heat capacity at constant volume, important for understanding fluid behavior in hypersonic flows.ⓘ Specific Heat Ratio [Y]			+10% -10%

✖The Parallel Upstream Flow Components is the set of flow characteristics that exist before an oblique shock wave, influencing the behavior of hypersonic flows.ⓘ Parallel Upstream Flow Components after Shock as Mach Tends to Infinite [u2]

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Parallel Upstream Flow Components after Shock as Mach Tends to Infinite Solution

STEP 0: Pre-Calculation Summary

Formula Used

Parallel Upstream Flow Components = Velocity of the fluid at 1*(1-(2*(sin(Wave Angle))^2)/(Specific Heat Ratio-1))
u2 = V₁*(1-(2*(sin(β))^2)/(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

Parallel Upstream Flow Components - (Measured in Meter per Second) - The Parallel Upstream Flow Components is the set of flow characteristics that exist before an oblique shock wave, influencing the behavior of hypersonic flows.
Velocity of the fluid at 1 - (Measured in Meter per Second) - The Velocity of the fluid at 1 is the speed of the fluid at a specific point in a flow system, crucial for analyzing fluid behavior in various applications.
Wave Angle - (Measured in Radian) - The Wave Angle is the angle between the direction of a hypersonic flow and the wave generated by an oblique shock in fluid mechanics.
Specific Heat Ratio - The Specific Heat Ratio is the ratio of the heat capacity at constant pressure to the heat capacity at constant volume, important for understanding fluid behavior in hypersonic flows.

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: 0.5 Radian --> 0.5 Radian No Conversion Required
Specific Heat Ratio: 1.6 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

u2 = V₁*(1-(2*(sin(β))^2)/(Y-1)) --> 26.2*(1-(2*(sin(0.5))^2)/(1.6-1))

Evaluating ... ...

u2 = 6.12653402290877

STEP 3: Convert Result to Output's Unit

6.12653402290877 Meter per Second --> No Conversion Required

FINAL ANSWER

6.12653402290877 ≈ 6.126534 Meter per Second <-- Parallel Upstream Flow Components

(Calculation completed in 00.018 seconds)

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Created by Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

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PSG College of Technology (PSGCT), Coimbatore

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< Oblique Shock Relation Calculators

Parallel Upstream Flow Components after Shock as Mach Tends to Infinite

LaTeX 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)

Wave Angle for Small Deflection Angle

LaTeX Go Wave Angle = (Specific Heat Ratio+1)/2*(Deflection Angle*180/pi)*pi/180

Coefficient of Pressure Derived from Oblique Shock Theory

LaTeX Go Pressure Coefficient = 2*(sin(Wave Angle))^2

Parallel Upstream Flow Components after Shock as Mach Tends to Infinite Formula

LaTeX Go

Parallel Upstream Flow Components = Velocity of the fluid at 1*(1-(2*(sin(Wave Angle))^2)/(Specific Heat Ratio-1))
u2 = V₁*(1-(2*(sin(β))^2)/(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 Parallel Upstream Flow Components after Shock as Mach Tends to Infinite?

Parallel Upstream Flow Components after Shock as Mach Tends to Infinite calculator uses Parallel Upstream Flow Components = Velocity of the fluid at 1*(1-(2*(sin(Wave Angle))^2)/(Specific Heat Ratio-1)) to calculate the Parallel Upstream Flow Components, Parallel Upstream Flow Components after Shock as Mach Tends to Infinite formula is defined as a measure of the upstream flow velocity component parallel to the shock wave direction in an oblique shock wave, which is a fundamental concept in aerodynamics and aerospace engineering, used to analyze high-speed flow phenomena. Parallel Upstream Flow Components is denoted by u2 symbol.

How to calculate Parallel Upstream Flow Components after Shock as Mach Tends to Infinite using this online calculator? To use this online calculator for Parallel Upstream Flow Components after Shock as Mach Tends to Infinite, enter Velocity of the fluid at 1 (V₁), Wave Angle (β) & Specific Heat Ratio (Y) and hit the calculate button. Here is how the Parallel Upstream Flow Components after Shock as Mach Tends to Infinite calculation can be explained with given input values -> 6.126534 = 26.2*(1-(2*(sin(0.5))^2)/(1.6-1)).

FAQ

What is Parallel Upstream Flow Components after Shock as Mach Tends to Infinite?

Parallel Upstream Flow Components after Shock as Mach Tends to Infinite formula is defined as a measure of the upstream flow velocity component parallel to the shock wave direction in an oblique shock wave, which is a fundamental concept in aerodynamics and aerospace engineering, used to analyze high-speed flow phenomena and is represented as u2 = V₁*(1-(2*(sin(β))^2)/(Y-1)) or Parallel Upstream Flow Components = Velocity of the fluid at 1*(1-(2*(sin(Wave Angle))^2)/(Specific Heat Ratio-1)). The Velocity of the fluid at 1 is the speed of the fluid at a specific point in a flow system, crucial for analyzing fluid behavior in various applications, The Wave Angle is the angle between the direction of a hypersonic flow and the wave generated by an oblique shock in fluid mechanics & The Specific Heat Ratio is the ratio of the heat capacity at constant pressure to the heat capacity at constant volume, important for understanding fluid behavior in hypersonic flows.

How to calculate Parallel Upstream Flow Components after Shock as Mach Tends to Infinite?

Parallel Upstream Flow Components after Shock as Mach Tends to Infinite formula is defined as a measure of the upstream flow velocity component parallel to the shock wave direction in an oblique shock wave, which is a fundamental concept in aerodynamics and aerospace engineering, used to analyze high-speed flow phenomena is calculated using Parallel Upstream Flow Components = Velocity of the fluid at 1*(1-(2*(sin(Wave Angle))^2)/(Specific Heat Ratio-1)). To calculate Parallel Upstream Flow Components after Shock as Mach Tends to Infinite, 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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