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Pressure Coefficient behind Oblique Shock Wave for Infinite Mach Number Formula

GoCoefficient of Pressure Derived from Oblique Shock Theory Formula

GoPressure Coefficient behind Oblique Shock Wave Formula

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The Pressure Coefficient is a dimensionless number that represents the relative pressure difference across a surface in fluid flow, indicating how pressure varies in different flow conditions. Check FAQs

C p = \frac{4}{Y + 1} \cdot {(\sin (β))}^{2}

C_p - Pressure Coefficient?Y - Specific Heat Ratio?β - Wave Angle?

Pressure Coefficient behind Oblique Shock Wave for Infinite Mach Number Example

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Here is how the Pressure Coefficient behind Oblique Shock Wave for Infinite Mach Number equation looks like with Values.

Here is how the Pressure Coefficient behind Oblique Shock Wave for Infinite Mach Number equation looks like with Units.

Here is how the Pressure Coefficient behind Oblique Shock Wave for Infinite Mach Number equation looks like.

0.3536 = \frac{4}{1.6 + 1} \cdot {(\sin (0.5))}^{2}

0.3536 = \frac{4}{1.6 + 1} \cdot {(\sin (0.5rad))}^{2}

0.3536 = \frac{4}{1.6 + 1} \cdot {(\sin (0.5))}^{2}

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Pressure Coefficient behind Oblique Shock Wave for Infinite Mach Number Solution

Follow our step by step solution on how to calculate Pressure Coefficient behind Oblique Shock Wave for Infinite Mach Number?

FIRST Step Consider the formula

C p = \frac{4}{Y + 1} \cdot {(\sin (β))}^{2}

Next Step Substitute values of Variables

∴

C p = \frac{4}{1.6 + 1} \cdot {(\sin (0.5rad))}^{2}

Next Step Prepare to Evaluate

∴

C p = \frac{4}{1.6 + 1} \cdot {(\sin (0.5))}^{2}

Next Step Evaluate

∴

C p = 0.353613610870662

LAST Step Rounding Answer

∴

C p = 0.3536

Pressure Coefficient behind Oblique Shock Wave for Infinite Mach Number Formula Elements

Variables

Functions

Pressure Coefficient

The Pressure Coefficient is a dimensionless number that represents the relative pressure difference across a surface in fluid flow, indicating how pressure varies in different flow conditions.

Symbol: C_p

Measurement: NAUnit: Unitless

Note: Value can be positive or negative.

Formulas to find Pressure Coefficient

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.

Symbol: Y

Measurement: NAUnit: Unitless

Note: Value can be positive or negative.

Formulas to find Specific Heat Ratio

Wave Angle

The Wave Angle is the angle between the direction of a hypersonic flow and the wave generated by an oblique shock in fluid mechanics.

Symbol: β

Measurement: AngleUnit: rad

Note: Value should be greater than 0.

Formulas to find Wave Angle

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 Pressure Coefficient

Go Coefficient of Pressure Derived from Oblique Shock Theory

C p = 2 \cdot {(\sin (β))}^{2}

Go Pressure Coefficient behind Oblique Shock Wave

C p = \frac{4}{Y + 1} \cdot ({(\sin (β))}^{2} - \frac{1}{M^{2}})

Go Non-Dimensional Pressure Coefficient

C p = \frac{Δp}{P dynamic}

Other formulas in Oblique Shock Relation category

Go Wave Angle for Small Deflection Angle

β = \frac{Y + 1}{2} \cdot (θ d \cdot \frac{180}{π}) \cdot \frac{π}{180}

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

u2 = V 1 \cdot (1 - \frac{2 \cdot {(\sin (β))}^{2}}{Y - 1})

Go Perpendicular Upstream Flow Components behind Shock Wave

v2 = \frac{V 1 \cdot (\sin (2 \cdot β))}{Y - 1}

Go Exact Pressure Ratio

r p = 1 + 2 \cdot \frac{Y}{Y + 1} \cdot ({(M \cdot \sin (β))}^{2} - 1)

How to Evaluate Pressure Coefficient behind Oblique Shock Wave for Infinite Mach Number?

Pressure Coefficient behind Oblique Shock Wave for Infinite Mach Number evaluator uses Pressure Coefficient = 4/(Specific Heat Ratio+1)*(sin(Wave Angle))^2 to evaluate the Pressure Coefficient, Pressure Coefficient behind Oblique Shock Wave for Infinite Mach Number formula is defined as a dimensionless quantity that characterizes the pressure ratio across an oblique shock wave in a supersonic flow, providing a crucial parameter in the analysis of high-speed aerodynamics and aerospace engineering applications. Pressure Coefficient is denoted by C_p symbol.

How to evaluate Pressure Coefficient behind Oblique Shock Wave for Infinite Mach Number using this online evaluator? To use this online evaluator for Pressure Coefficient behind Oblique Shock Wave for Infinite Mach Number, enter Specific Heat Ratio (Y) & Wave Angle (β) and hit the calculate button.

FAQs on Pressure Coefficient behind Oblique Shock Wave for Infinite Mach Number

What is the formula to find Pressure Coefficient behind Oblique Shock Wave for Infinite Mach Number?

The formula of Pressure Coefficient behind Oblique Shock Wave for Infinite Mach Number is expressed as Pressure Coefficient = 4/(Specific Heat Ratio+1)*(sin(Wave Angle))^2. Here is an example- 0.353614 = 4/(1.6+1)*(sin(0.5))^2.

How to calculate Pressure Coefficient behind Oblique Shock Wave for Infinite Mach Number?

With Specific Heat Ratio (Y) & Wave Angle (β) we can find Pressure Coefficient behind Oblique Shock Wave for Infinite Mach Number using the formula - Pressure Coefficient = 4/(Specific Heat Ratio+1)*(sin(Wave Angle))^2. This formula also uses Sine (sin) function(s).

What are the other ways to Calculate Pressure Coefficient?

Here are the different ways to Calculate Pressure Coefficient-

Pressure Coefficient=2*(sin(Wave Angle))^2
Pressure Coefficient=4/(Specific Heat Ratio+1)*((sin(Wave Angle))^2-1/Mach Number^2)
Pressure Coefficient=Change in Static Pressure/Dynamic Pressure

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