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

GoComponent of Downstream Mach Normal to Oblique Shock Formula

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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. Check FAQs

M n2 = \sqrt{\frac{1 + 0.5 \cdot (γ o - 1) \cdot {M n1}^{2}}{γ o \cdot {M n1}^{2} - 0.5 \cdot (γ o - 1)}}

M_n2 - Downstream Mach Normal to Oblique Shock?γ_o - Specific Heat Ratio Oblique Shock?M_n1 - Upstream Mach Normal to Oblique Shock?

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

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Here is how the Component of Downstream Mach Number Normal to Oblique Shock for given Normal Upstream Mach Number equation looks like with Values.

Here is how the Component of Downstream Mach Number Normal to Oblique Shock for given Normal Upstream Mach Number equation looks like with Units.

Here is how the Component of Downstream Mach Number Normal to Oblique Shock for given Normal Upstream Mach Number equation looks like.

0.6666 = \sqrt{\frac{1 + 0.5 \cdot (1.4 - 1) \cdot {1.606}^{2}}{1.4 \cdot {1.606}^{2} - 0.5 \cdot (1.4 - 1)}}

0.6666 = \sqrt{\frac{1 + 0.5 \cdot (1.4 - 1) \cdot {1.606}^{2}}{1.4 \cdot {1.606}^{2} - 0.5 \cdot (1.4 - 1)}}

0.6666 = \sqrt{\frac{1 + 0.5 \cdot (1.4 - 1) \cdot {1.606}^{2}}{1.4 \cdot {1.606}^{2} - 0.5 \cdot (1.4 - 1)}}

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

Follow our step by step solution on how to calculate Component of Downstream Mach Number Normal to Oblique Shock for given Normal Upstream Mach Number?

FIRST Step Consider the formula

M n2 = \sqrt{\frac{1 + 0.5 \cdot (γ o - 1) \cdot {M n1}^{2}}{γ o \cdot {M n1}^{2} - 0.5 \cdot (γ o - 1)}}

Next Step Substitute values of Variables

∴

M n2 = \sqrt{\frac{1 + 0.5 \cdot (1.4 - 1) \cdot {1.606}^{2}}{1.4 \cdot {1.606}^{2} - 0.5 \cdot (1.4 - 1)}}

Next Step Prepare to Evaluate

∴

M n2 = \sqrt{\frac{1 + 0.5 \cdot (1.4 - 1) \cdot {1.606}^{2}}{1.4 \cdot {1.606}^{2} - 0.5 \cdot (1.4 - 1)}}

Next Step Evaluate

∴

M n2 = 0.666639869920256

LAST Step Rounding Answer

∴

M n2 = 0.6666

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

Variables

Functions

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.

Symbol: M_n2

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Downstream Mach Normal to Oblique Shock

Specific Heat Ratio Oblique Shock

The Specific Heat Ratio Oblique Shock is the ratio of the heat capacity at constant pressure to heat capacity at constant volume.

Symbol: γ_o

Measurement: NAUnit: Unitless

Note: Value should be greater than 1.

Formulas to find Specific Heat Ratio Oblique Shock

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.

Symbol: M_n1

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Upstream Mach Normal to Oblique Shock

sqrt

A square root function is a function that takes a non-negative number as an input and returns the square root of the given input number.

Syntax: sqrt(Number)

Other Formulas to find Downstream Mach Normal to Oblique Shock

Go Component of Downstream Mach Normal to Oblique Shock

M n2 = M 2 \cdot \sin (β - θ)

Other formulas in Oblique Shock category

Go Component of Upstream Mach Normal to Oblique Shock

M n1 = M 1 \cdot \sin (β)

Go Flow Deflection Angle due to Oblique Shock

θ = a \tan (\frac{2 \cdot \cot (β) \cdot ({(M 1 \cdot \sin (β))}^{2} - 1)}{{M 1}^{2} \cdot (γ o + \cos (2 \cdot β)) + 2})

Go Density Ratio across Oblique Shock

ρ r = (γ o + 1) \cdot \frac{{M n1}^{2}}{2 + (γ o - 1) \cdot {M n1}^{2}}

Go Pressure Ratio across Oblique Shock

P r = 1 + (\frac{2 \cdot γ o}{γ o + 1}) \cdot ({M n1}^{2} - 1)

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

Component of Downstream Mach Number Normal to Oblique Shock for given Normal Upstream Mach Number evaluator uses 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))) to evaluate the Downstream Mach Normal to Oblique Shock, The Component of Downstream Mach Number Normal to Oblique Shock for given Normal Upstream Mach Number formula calculates the downstream Mach number component perpendicular to an oblique shock wave, given the upstream Mach number. It reveals how this downstream Mach number is influenced by the initial Mach number and the shock geometry. Downstream Mach Normal to Oblique Shock is denoted by M_n2 symbol.

How to evaluate Component of Downstream Mach Number Normal to Oblique Shock for given Normal Upstream Mach Number using this online evaluator? To use this online evaluator for Component of Downstream Mach Number Normal to Oblique Shock for given Normal Upstream Mach Number, enter Specific Heat Ratio Oblique Shock (γ_o) & Upstream Mach Normal to Oblique Shock (M_n1) and hit the calculate button.

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

What is the formula to find Component of Downstream Mach Number Normal to Oblique Shock for given Normal Upstream Mach Number?

The formula of Component of Downstream Mach Number Normal to Oblique Shock for given Normal Upstream Mach Number is expressed as 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))). Here is an example- 0.66664 = sqrt((1+0.5*(1.4-1)*1.606^2)/(1.4*1.606^2-0.5*(1.4-1))).

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

With Specific Heat Ratio Oblique Shock (γ_o) & Upstream Mach Normal to Oblique Shock (M_n1) we can find Component of Downstream Mach Number Normal to Oblique Shock for given Normal Upstream Mach Number using the formula - 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))). This formula also uses Square Root (sqrt) function(s).

What are the other ways to Calculate Downstream Mach Normal to Oblique Shock?

Here are the different ways to Calculate Downstream Mach Normal to Oblique Shock-

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

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

​GoComponent of Downstream Mach Normal to Oblique Shock Formula

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

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

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

Other Formulas to find Downstream Mach Normal to Oblique Shock

Other formulas in Oblique Shock category

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

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

Variable Name

GoComponent of Downstream Mach Normal to Oblique Shock Formula