Component of Downstream Mach Normal to Oblique Shock Calculator

✖Mach Number Behind Oblique Shock represents the velocity of a fluid or airflow relative to the speed of sound after passing through an oblique shock wave.ⓘ Mach Number Behind Oblique Shock [M₂]			+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%
✖Flow Deflection Angle Oblique Shock is defined as the angle by which the flow turns towards the oblique shock.ⓘ Flow Deflection Angle Oblique Shock [θ]			+10% -10%

✖Downstream Mach Normal to Oblique Shock denotes the Mach number component aligned with the shock wave's normal direction after passing through an oblique shock.ⓘ Component of Downstream Mach Normal to Oblique Shock [M_n2]

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Component of Downstream Mach Normal to Oblique Shock Solution

STEP 0: Pre-Calculation Summary

Formula Used

Downstream Mach Normal to Oblique Shock = Mach Number Behind Oblique Shock*sin(Oblique Shock Angle-Flow Deflection Angle Oblique Shock)
M_n2 = M₂*sin(β-θ)
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

Downstream Mach Normal to Oblique Shock - Downstream Mach Normal to Oblique Shock denotes the Mach number component aligned with the shock wave's normal direction after passing through an oblique shock.
Mach Number Behind Oblique Shock - Mach Number Behind Oblique Shock represents the velocity of a fluid or airflow relative to the speed of sound after passing through 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.
Flow Deflection Angle Oblique Shock - (Measured in Radian) - Flow Deflection Angle Oblique Shock is defined as the angle by which the flow turns towards the oblique shock.

STEP 1: Convert Input(s) to Base Unit

Mach Number Behind Oblique Shock: 1.21 --> No Conversion Required
Oblique Shock Angle: 53.4 Degree --> 0.932005820564797 Radian (Check conversion here)
Flow Deflection Angle Oblique Shock: 20 Degree --> 0.3490658503988 Radian (Check conversion here)

STEP 2: Evaluate Formula

Substituting Input Values in Formula

M_n2 = M₂*sin(β-θ) --> 1.21*sin(0.932005820564797-0.3490658503988)

Evaluating ... ...

M_n2 = 0.666081695502734

STEP 3: Convert Result to Output's Unit

0.666081695502734 --> No Conversion Required

FINAL ANSWER

0.666081695502734 ≈ 0.666082 <-- Downstream Mach Normal to Oblique Shock

(Calculation completed in 00.004 seconds)

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Created by Vinay Mishra

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

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Vallurupalli Nageswara Rao Vignana Jyothi Institute of Engineering and Technology (VNRVJIET), Hyderabad

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< Oblique Shock Calculators

Flow Deflection Angle due to Oblique Shock

LaTeX 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))

Density Ratio across Oblique Shock

LaTeX 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

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

Component of Upstream Mach Normal to Oblique Shock

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

Component of Downstream Mach Normal to Oblique Shock Formula

LaTeX Go

Downstream Mach Normal to Oblique Shock = Mach Number Behind Oblique Shock*sin(Oblique Shock Angle-Flow Deflection Angle Oblique Shock)
M_n2 = M₂*sin(β-θ)

Is it possible to correlate Oblique and Normal Shock?

It is always possible to convert an oblique shock into a normal shock by a Galilean transformation. In physics, a Galilean transformation is used to transform between the coordinates of two reference frames which differ only by constant relative motion within the constructs of Newtonian physics.

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

Component of Downstream Mach Normal to Oblique Shock calculator uses Downstream Mach Normal to Oblique Shock = Mach Number Behind Oblique Shock*sin(Oblique Shock Angle-Flow Deflection Angle Oblique Shock) to calculate the Downstream Mach Normal to Oblique Shock, The Component of Downstream Mach Normal to Oblique Shock defines the downstream Mach number normal to an oblique shock wave, representing the Mach number component perpendicular to the shock. It shows how this downstream Mach number is influenced by the upstream Mach number and the angles of the shock wave and flow deflection. Downstream Mach Normal to Oblique Shock is denoted by M_n2 symbol.

How to calculate Component of Downstream Mach Normal to Oblique Shock using this online calculator? To use this online calculator for Component of Downstream Mach Normal to Oblique Shock, enter Mach Number Behind Oblique Shock (M₂), Oblique Shock Angle (β) & Flow Deflection Angle Oblique Shock (θ) and hit the calculate button. Here is how the Component of Downstream Mach Normal to Oblique Shock calculation can be explained with given input values -> 0.666082 = 1.21*sin(0.932005820564797-0.3490658503988).

FAQ

What is Component of Downstream Mach Normal to Oblique Shock?

The Component of Downstream Mach Normal to Oblique Shock defines the downstream Mach number normal to an oblique shock wave, representing the Mach number component perpendicular to the shock. It shows how this downstream Mach number is influenced by the upstream Mach number and the angles of the shock wave and flow deflection and is represented as M_n2 = M₂*sin(β-θ) or Downstream Mach Normal to Oblique Shock = Mach Number Behind Oblique Shock*sin(Oblique Shock Angle-Flow Deflection Angle Oblique Shock). Mach Number Behind Oblique Shock represents the velocity of a fluid or airflow relative to the speed of sound after passing through 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 & Flow Deflection Angle Oblique Shock is defined as the angle by which the flow turns towards the oblique shock.

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

The Component of Downstream Mach Normal to Oblique Shock defines the downstream Mach number normal to an oblique shock wave, representing the Mach number component perpendicular to the shock. It shows how this downstream Mach number is influenced by the upstream Mach number and the angles of the shock wave and flow deflection is calculated using Downstream Mach Normal to Oblique Shock = Mach Number Behind Oblique Shock*sin(Oblique Shock Angle-Flow Deflection Angle Oblique Shock). To calculate Component of Downstream Mach Normal to Oblique Shock, you need Mach Number Behind Oblique Shock (M₂), Oblique Shock Angle (β) & Flow Deflection Angle Oblique Shock (θ). With our tool, you need to enter the respective value for Mach Number Behind Oblique Shock, Oblique Shock Angle & Flow Deflection Angle Oblique Shock and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

How many ways are there to calculate Downstream Mach Normal to Oblique Shock?

In this formula, Downstream Mach Normal to Oblique Shock uses Mach Number Behind Oblique Shock, Oblique Shock Angle & Flow Deflection Angle Oblique Shock. We can use 1 other way(s) to calculate the same, which is/are as follows -

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)))

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