FormulaDen.com

Physics Chemistry Math Chemical Engineering Civil Electrical Electronics Electronics and Instrumentation Materials Science Mechanical Production Engineering Financial Health

Component of Downstream Mach Normal to Oblique Shock Formula

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

Fx Copy

LaTeX Copy

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 = M 2 \cdot \sin (β - θ)

M_n2 - Downstream Mach Normal to Oblique Shock?M₂ - Mach Number Behind Oblique Shock?β - Oblique Shock Angle?θ - Flow Deflection Angle Oblique Shock?

Component of Downstream Mach Normal to Oblique Shock Example

With values

With units

Only example

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

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

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

0.6661 = 1.21 \cdot \sin (53.4 - 20)

0.6661 = 1.21 \cdot \sin (53.4° - 20°)

0.6661 = 1.21 \cdot \sin (53.4 - 20)

Tip: Use pencil ( Pencil

) icon above to edit Input Values and Units.

Calculate

Recalculate

Solution

Copy

Reset

You are here -

Home » Category

Physics » Category

Aerospace » Category

Aerodynamics » fx Component of Downstream Mach Normal to Oblique Shock

Component of Downstream Mach Normal to Oblique Shock Solution

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

FIRST Step Consider the formula

M n2 = M 2 \cdot \sin (β - θ)

Next Step Substitute values of Variables

∴

M n2 = 1.21 \cdot \sin (53.4° - 20°)

Next Step Convert Units

∴

M n2 = 1.21 \cdot \sin (0.932rad - 0.3491rad)

Next Step Prepare to Evaluate

∴

M n2 = 1.21 \cdot \sin (0.932 - 0.3491)

Next Step Evaluate

∴

M n2 = 0.666081695502734

LAST Step Rounding Answer

∴

M n2 = 0.6661

Component of Downstream Mach Normal to Oblique Shock 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

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.

Symbol: M₂

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Mach Number Behind Oblique Shock

Oblique Shock Angle

Oblique Shock Angle signifies the angle formed by the direction of an incoming airflow or fluid with respect to the oblique shock wave.

Symbol: β

Measurement: AngleUnit: °

Note: Value should be less than 91.

Formulas to find Oblique Shock Angle

Flow Deflection Angle Oblique Shock

Flow Deflection Angle Oblique Shock is defined as the angle by which the flow turns towards the oblique shock.

Symbol: θ

Measurement: AngleUnit: °

Note: Value can be positive or negative.

Formulas to find Flow Deflection Angle Oblique Shock

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.

Syntax: sin(Angle)

Other Formulas to find Downstream Mach Normal to Oblique Shock

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

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)}}

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 Normal to Oblique Shock?

Component of Downstream Mach Normal to Oblique Shock evaluator uses Downstream Mach Normal to Oblique Shock = Mach Number Behind Oblique Shock*sin(Oblique Shock Angle-Flow Deflection Angle Oblique Shock) to evaluate 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 evaluate Component of Downstream Mach Normal to Oblique Shock using this online evaluator? To use this online evaluator 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.

FAQs on Component of Downstream Mach Normal to Oblique Shock

What is the formula to find Component of Downstream Mach Normal to Oblique Shock?

The formula of Component of Downstream Mach Normal to Oblique Shock is expressed as Downstream Mach Normal to Oblique Shock = Mach Number Behind Oblique Shock*sin(Oblique Shock Angle-Flow Deflection Angle Oblique Shock). Here is an example- 0.666082 = 1.21*sin(0.932005820564797-0.3490658503988).

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

With Mach Number Behind Oblique Shock (M₂), Oblique Shock Angle (β) & Flow Deflection Angle Oblique Shock (θ) we can find Component of Downstream Mach Normal to Oblique Shock using the formula - Downstream Mach Normal to Oblique Shock = Mach Number Behind Oblique Shock*sin(Oblique Shock Angle-Flow Deflection Angle Oblique Shock). This formula also uses Sine (sin) 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=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)))

Let Others Know

✖

Facebook

Twitter

Copied!

: Value
: Unit