Component of Upstream Mach Normal to Oblique Shock Calculator

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Compressible Flow

Fundamentals of Inviscid and Incompressible Flow

Three-Dimensional Incompressible Flow

Two-Dimensional Incompressible Flow

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Oblique Shock and Expansion Waves

Governing Equations and Sound Wave

Normal Shock Wave

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Oblique Shock

Expansion Waves

✖Mach Number Ahead of Oblique Shock signifies the velocity of a fluid or airflow relative to the speed of sound before encountering an oblique shock wave.ⓘ Mach Number Ahead of Oblique Shock [M₁]			+10% -10%
✖Oblique Shock Angle signifies the angle formed by the direction of an incoming airflow or fluid with respect to the oblique shock wave.ⓘ Oblique Shock Angle [β]			+10% -10%

✖Upstream Mach Normal to Oblique Shock represents the Mach number's component aligned with the shock wave's normal direction.ⓘ Component of Upstream Mach Normal to Oblique Shock [M_n1]

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Formula

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Component of Upstream Mach Normal to Oblique Shock

Formula

`"M"_{"n1"} = "M"_{"1"}*sin("β")`

Example

`"1.605635"="2"*sin("53.4°")`

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Download Oblique Shock and Expansion Waves Formulas PDF

Component of Upstream Mach Normal to Oblique Shock Solution

STEP 0: Pre-Calculation Summary

Formula Used

Upstream Mach Normal to Oblique Shock = Mach Number Ahead of Oblique Shock*sin(Oblique Shock Angle)
M_n1 = M₁*sin(β)
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

Upstream Mach Normal to Oblique Shock - Upstream Mach Normal to Oblique Shock represents the Mach number's component aligned with the shock wave's normal direction.
Mach Number Ahead of Oblique Shock - Mach Number Ahead of Oblique Shock signifies the velocity of a fluid or airflow relative to the speed of sound before encountering an oblique shock wave.
Oblique Shock Angle - (Measured in Radian) - Oblique Shock Angle signifies the angle formed by the direction of an incoming airflow or fluid with respect to the oblique shock wave.

STEP 1: Convert Input(s) to Base Unit

Mach Number Ahead of Oblique Shock: 2 --> No Conversion Required
Oblique Shock Angle: 53.4 Degree --> 0.932005820564797 Radian (Check conversion here)

STEP 2: Evaluate Formula

Substituting Input Values in Formula

M_n1 = M₁*sin(β) --> 2*sin(0.932005820564797)

Evaluating ... ...

M_n1 = 1.60563495038202

STEP 3: Convert Result to Output's Unit

1.60563495038202 --> No Conversion Required

FINAL ANSWER

1.60563495038202 ≈ 1.605635 <-- Upstream Mach Normal to Oblique Shock

(Calculation completed in 00.004 seconds)

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Credits

Created by Vinay Mishra

Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune

Vinay Mishra has created this Calculator and 300+ more calculators!

Verified by Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

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< 10+ Oblique Shock Calculators

Temperature behind Oblique Shock for given Upstream Temperature and Normal Upstream Mach Number

Go Temperature Behind Oblique Shock = Temperature Ahead of Oblique Shock*((1+((2*Specific Heat Ratio Oblique Shock)/(Specific Heat Ratio Oblique Shock+1))*(Upstream Mach Normal to Oblique Shock^2-1))/((Specific Heat Ratio Oblique Shock+1)*(Upstream Mach Normal to Oblique Shock^2)/(2+(Specific Heat Ratio Oblique Shock-1)*Upstream Mach Normal to Oblique Shock^2)))

Flow Deflection Angle due to Oblique Shock

Go Flow Deflection Angle Oblique Shock = atan((2*cot(Oblique Shock Angle)*((Mach Number Ahead of Oblique Shock*sin(Oblique Shock Angle))^2-1))/(Mach Number Ahead of Oblique Shock^2*(Specific Heat Ratio Oblique Shock+cos(2*Oblique Shock Angle))+2))

Temperature Ratio across Oblique Shock

Go Temperature Ratio Across Oblique Shock = (1+((2*Specific Heat Ratio Oblique Shock)/(Specific Heat Ratio Oblique Shock+1))*(Upstream Mach Normal to Oblique Shock^2-1))/((Specific Heat Ratio Oblique Shock+1)*(Upstream Mach Normal to Oblique Shock^2)/(2+(Specific Heat Ratio Oblique Shock-1)*Upstream Mach Normal to Oblique Shock^2))

Component of Downstream Mach Number Normal to Oblique Shock for given Normal Upstream Mach Number

Go Downstream Mach Normal to Oblique Shock = sqrt((1+0.5*(Specific Heat Ratio Oblique Shock-1)*Upstream Mach Normal to Oblique Shock^2)/(Specific Heat Ratio Oblique Shock*Upstream Mach Normal to Oblique Shock^2-0.5*(Specific Heat Ratio Oblique Shock-1)))

Density behind Oblique Shock for given Upstream Density and Normal Upstream Mach Number

Go Density Behind Oblique Shock = Density Ahead of Oblique Shock*((Specific Heat Ratio Oblique Shock+1)*(Upstream Mach Normal to Oblique Shock^2)/(2+(Specific Heat Ratio Oblique Shock-1)*Upstream Mach Normal to Oblique Shock^2))

Pressure behind Oblique Shock for given Upstream Pressure and Normal Upstream Mach Number

Go Static Pressure Behind Oblique Shock = Static Pressure Ahead of Oblique Shock*(1+((2*Specific Heat Ratio Oblique Shock)/(Specific Heat Ratio Oblique Shock+1))*(Upstream Mach Normal to Oblique Shock^2-1))

Density Ratio across Oblique Shock

Go Density Ratio Across Oblique Shock = (Specific Heat Ratio Oblique Shock+1)*(Upstream Mach Normal to Oblique Shock^2)/(2+(Specific Heat Ratio Oblique Shock-1)*Upstream Mach Normal to Oblique Shock^2)

Component of Downstream Mach Normal to Oblique Shock

Go Downstream Mach Normal to Oblique Shock = Mach Number Behind Oblique Shock*sin(Oblique Shock Angle-Flow Deflection Angle Oblique Shock)

Pressure Ratio across Oblique Shock

Go Pressure Ratio Across Oblique Shock = 1+((2*Specific Heat Ratio Oblique Shock)/(Specific Heat Ratio Oblique Shock+1))*(Upstream Mach Normal to Oblique Shock^2-1)

Component of Upstream Mach Normal to Oblique Shock

Go Upstream Mach Normal to Oblique Shock = Mach Number Ahead of Oblique Shock*sin(Oblique Shock Angle)

Component of Upstream Mach Normal to Oblique Shock Formula

Upstream Mach Normal to Oblique Shock = Mach Number Ahead of Oblique Shock*sin(Oblique Shock Angle)
M_n1 = M₁*sin(β)

What is an Oblique Shock?

An oblique shock wave is a shock wave that, unlike a normal shock, is inclined with respect to the incident upstream flow direction. It will occur when a supersonic flow encounters a corner that effectively turns the flow into itself and compresses.

How to Calculate Component of Upstream Mach Normal to Oblique Shock?

Component of Upstream Mach Normal to Oblique Shock calculator uses Upstream Mach Normal to Oblique Shock = Mach Number Ahead of Oblique Shock*sin(Oblique Shock Angle) to calculate the Upstream Mach Normal to Oblique Shock, The Component of Upstream Mach Normal to Oblique Shock formula defines the Mach number component of the flow in the direction perpendicular to an oblique shock wave at the upstream condition this formula is crucial for analyzing supersonic flows encountering oblique shock waves. Upstream Mach Normal to Oblique Shock is denoted by M_n1 symbol.

How to calculate Component of Upstream Mach Normal to Oblique Shock using this online calculator? To use this online calculator for Component of Upstream Mach Normal to Oblique Shock, enter Mach Number Ahead of Oblique Shock (M₁) & Oblique Shock Angle (β) and hit the calculate button. Here is how the Component of Upstream Mach Normal to Oblique Shock calculation can be explained with given input values -> 1.605635 = 2*sin(0.932005820564797).

FAQ

What is Component of Upstream Mach Normal to Oblique Shock?

The Component of Upstream Mach Normal to Oblique Shock formula defines the Mach number component of the flow in the direction perpendicular to an oblique shock wave at the upstream condition this formula is crucial for analyzing supersonic flows encountering oblique shock waves and is represented as M_n1 = M₁*sin(β) or Upstream Mach Normal to Oblique Shock = Mach Number Ahead of Oblique Shock*sin(Oblique Shock Angle). Mach Number Ahead of Oblique Shock signifies the velocity of a fluid or airflow relative to the speed of sound before encountering an oblique shock wave & Oblique Shock Angle signifies the angle formed by the direction of an incoming airflow or fluid with respect to the oblique shock wave.

How to calculate Component of Upstream Mach Normal to Oblique Shock?

The Component of Upstream Mach Normal to Oblique Shock formula defines the Mach number component of the flow in the direction perpendicular to an oblique shock wave at the upstream condition this formula is crucial for analyzing supersonic flows encountering oblique shock waves is calculated using Upstream Mach Normal to Oblique Shock = Mach Number Ahead of Oblique Shock*sin(Oblique Shock Angle). To calculate Component of Upstream Mach Normal to Oblique Shock, you need Mach Number Ahead of Oblique Shock (M₁) & Oblique Shock Angle (β). With our tool, you need to enter the respective value for Mach Number Ahead of Oblique Shock & Oblique Shock Angle 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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