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Pressure Coefficient for Blast Wave Theory at Very High Values of Mach Formula

GoPressure Coefficient Combined with Blast Wave for Shuttle at Angle of Attack Formula

GoPressure Coefficient for Blunt-Nosed Plate Formula

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Pressure coefficient defines the value of local pressure at a point in terms of free stream pressure and dynamic pressure. Check FAQs

C p = \frac{2}{Y \cdot M^{2}} \cdot r p

C_p - Pressure Coefficient?Y - Specific Heat Ratio?M - Mach Number?r_p - Pressure Ratio?

Pressure Coefficient for Blast Wave Theory at Very High Values of Mach Example

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Here is how the Pressure Coefficient for Blast Wave Theory at Very High Values of Mach equation looks like with Values.

Here is how the Pressure Coefficient for Blast Wave Theory at Very High Values of Mach equation looks like with Units.

Here is how the Pressure Coefficient for Blast Wave Theory at Very High Values of Mach equation looks like.

0.1172 = \frac{2}{1.6 \cdot 8^{2}} \cdot 6

0.1172 = \frac{2}{1.6 \cdot 8^{2}} \cdot 6

0.1172 = \frac{2}{1.6 \cdot 8^{2}} \cdot 6

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Pressure Coefficient for Blast Wave Theory at Very High Values of Mach Solution

Follow our step by step solution on how to calculate Pressure Coefficient for Blast Wave Theory at Very High Values of Mach?

FIRST Step Consider the formula

C p = \frac{2}{Y \cdot M^{2}} \cdot r p

Next Step Substitute values of Variables

∴

C p = \frac{2}{1.6 \cdot 8^{2}} \cdot 6

Next Step Prepare to Evaluate

∴

C p = \frac{2}{1.6 \cdot 8^{2}} \cdot 6

Next Step Evaluate

∴

C p = 0.1171875

LAST Step Rounding Answer

∴

C p = 0.1172

Pressure Coefficient for Blast Wave Theory at Very High Values of Mach Formula Elements

Variables

Pressure Coefficient

Pressure coefficient defines the value of local pressure at a point in terms of free stream pressure and dynamic pressure.

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 of a gas is the ratio of the specific heat of the gas at a constant pressure to its specific heat at a constant volume.

Symbol: Y

Measurement: NAUnit: Unitless

Note: Value can be positive or negative.

Formulas to find Specific Heat Ratio

Mach Number

Mach number is a dimensionless quantity representing the ratio of flow velocity past a boundary to the local speed of sound.

Symbol: M

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Mach Number

Pressure Ratio

Pressure Ratio is ratio of final to initial pressure.

Symbol: r_p

Measurement: NAUnit: Unitless

Note: Value can be positive or negative.

Formulas to find Pressure Ratio

Other Formulas to find Pressure Coefficient

Go Pressure Coefficient Combined with Blast Wave for Shuttle at Angle of Attack

C p = \frac{0.0137}{\frac{y}{l}} + 2 \cdot {(\sin (α))}^{2}

Go Pressure Coefficient for Blunt-Nosed Plate

C p = 0.173 \cdot \frac{{C d}^{\frac{2}{3}}}{{(\frac{x}{d 1})}^{\frac{2}{3}}}

Go Pressure Coefficient for Blunt-Nosed Cylinder

C p = 0.096 \cdot \frac{{C d}^{\frac{1}{2}}}{\frac{x d}{d}}

Go Pressure Coefficient Combined with Blast Wave for Shuttle

C p = \frac{0.0137}{\frac{x d}{l}}

How to Evaluate Pressure Coefficient for Blast Wave Theory at Very High Values of Mach?

Pressure Coefficient for Blast Wave Theory at Very High Values of Mach evaluator uses Pressure Coefficient = 2/(Specific Heat Ratio*Mach Number^2)*Pressure Ratio to evaluate the Pressure Coefficient, Pressure Coefficient for Blast Wave Theory at Very High Values of Mach formula is defined as a dimensionless quantity that characterizes the pressure distribution in a blast wave at extremely high Mach numbers, providing valuable insights into the behavior of shock waves in various fields, including aerospace engineering and astrophysics. Pressure Coefficient is denoted by C_p symbol.

How to evaluate Pressure Coefficient for Blast Wave Theory at Very High Values of Mach using this online evaluator? To use this online evaluator for Pressure Coefficient for Blast Wave Theory at Very High Values of Mach, enter Specific Heat Ratio (Y), Mach Number (M) & Pressure Ratio (r_p) and hit the calculate button.

FAQs on Pressure Coefficient for Blast Wave Theory at Very High Values of Mach

What is the formula to find Pressure Coefficient for Blast Wave Theory at Very High Values of Mach?

The formula of Pressure Coefficient for Blast Wave Theory at Very High Values of Mach is expressed as Pressure Coefficient = 2/(Specific Heat Ratio*Mach Number^2)*Pressure Ratio. Here is an example- 0.117188 = 2/(1.6*8^2)*41.96.

How to calculate Pressure Coefficient for Blast Wave Theory at Very High Values of Mach?

With Specific Heat Ratio (Y), Mach Number (M) & Pressure Ratio (r_p) we can find Pressure Coefficient for Blast Wave Theory at Very High Values of Mach using the formula - Pressure Coefficient = 2/(Specific Heat Ratio*Mach Number^2)*Pressure Ratio.

What are the other ways to Calculate Pressure Coefficient?

Here are the different ways to Calculate Pressure Coefficient-

Pressure Coefficient=0.0137/(Distance from X-Axis/Length of Shuttle)+2*(sin(Angle of Attack))^2
Pressure Coefficient=0.173*(Drag Coefficient^(2/3))/((Distance from Y-Axis/Diameter 1)^(2/3))
Pressure Coefficient=0.096*(Drag Coefficient^(1/2))/(Distance from Nose Tip to Required Base Diameter/Diameter)

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Pressure Coefficient for Blast Wave Theory at Very High Values of Mach Formula

​GoPressure Coefficient Combined with Blast Wave for Shuttle at Angle of Attack Formula

​GoPressure Coefficient for Blunt-Nosed Plate Formula

Pressure Coefficient for Blast Wave Theory at Very High Values of Mach Example

Pressure Coefficient for Blast Wave Theory at Very High Values of Mach Solution

Pressure Coefficient for Blast Wave Theory at Very High Values of Mach Formula Elements

Other Formulas to find Pressure Coefficient

How to Evaluate Pressure Coefficient for Blast Wave Theory at Very High Values of Mach?

FAQs on Pressure Coefficient for Blast Wave Theory at Very High Values of Mach

Variable Name

GoPressure Coefficient Combined with Blast Wave for Shuttle at Angle of Attack Formula

GoPressure Coefficient for Blunt-Nosed Plate Formula