Pressure Coefficient for Blast Wave Theory Calculator

✖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.ⓘ Specific Heat Ratio [Y]			+10% -10%
✖Mach number is a dimensionless quantity representing the ratio of flow velocity past a boundary to the local speed of sound.ⓘ Mach Number [M]			+10% -10%
✖Pressure Ratio is ratio of final to initial pressure.ⓘ Pressure Ratio [r_p]			+10% -10%

✖Pressure coefficient defines the value of local pressure at a point in terms of free stream pressure and dynamic pressure.ⓘ Pressure Coefficient for Blast Wave Theory [C_p]

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Formula

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Pressure Coefficient for Blast Wave Theory

Formula

`"C"_{"p"} = 2/("Y"*"M"^2)*("r"_{"p"}-1)`

Example

`"0.097656"=2/("1.6"*("8")^2)*("6"-1)`

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Pressure Coefficient for Blast Wave Theory Solution

STEP 0: Pre-Calculation Summary

Formula Used

Pressure Coefficient = 2/(Specific Heat Ratio*Mach Number^2)*(Pressure Ratio-1)
C_p = 2/(Y*M^2)*(r_p-1)
This formula uses 4 Variables

Variables Used

Pressure Coefficient - Pressure coefficient defines the value of local pressure at a point in terms of free stream pressure and dynamic pressure.
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.
Mach Number - Mach number is a dimensionless quantity representing the ratio of flow velocity past a boundary to the local speed of sound.
Pressure Ratio - Pressure Ratio is ratio of final to initial pressure.

STEP 1: Convert Input(s) to Base Unit

Specific Heat Ratio: 1.6 --> No Conversion Required
Mach Number: 8 --> No Conversion Required
Pressure Ratio: 6 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_p = 2/(Y*M^2)*(r_p-1) --> 2/(1.6*8^2)*(6-1)

Evaluating ... ...

C_p = 0.09765625

STEP 3: Convert Result to Output's Unit

0.09765625 --> No Conversion Required

FINAL ANSWER

0.09765625 ≈ 0.097656 <-- Pressure Coefficient

(Calculation completed in 00.004 seconds)

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Home » Engineering » Mechanical » Fluid Mechanics » Hypersonic Flow » Blast Wave Part Theory » Pressure Coefficient for Blast Wave Theory

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Created by Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

Sanjay Krishna has created this Calculator and 300+ more calculators!

Verified by Maiarutselvan V

PSG College of Technology (PSGCT), Coimbatore

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< 6 Blast Wave Part Theory Calculators

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

Go Pressure Coefficient = 0.0137/(Distance from X-Axis/Length of Shuttle)+2*(sin(Angle of Attack))^2

Pressure Coefficient for Blunt-Nosed Cylinder

Go Pressure Coefficient = 0.096*(Drag Coefficient^(1/2))/(Distance from Nose Tip to Required Base Diameter/Diameter)

Pressure Coefficient for Blunt-Nosed Plate

Go Pressure Coefficient = 0.173*(Drag Coefficient^(2/3))/((Distance from Y-Axis/Diameter 1)^(2/3))

Pressure Coefficient for Blast Wave Theory

Go Pressure Coefficient = 2/(Specific Heat Ratio*Mach Number^2)*(Pressure Ratio-1)

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

Go Pressure Coefficient = 2/(Specific Heat Ratio*Mach Number^2)*Pressure Ratio

Pressure Coefficient Combined with Blast Wave for Shuttle

Go Pressure Coefficient = 0.0137/(Distance from Nose Tip to Required Base Diameter/Length of Shuttle)

Pressure Coefficient for Blast Wave Theory Formula

Pressure Coefficient = 2/(Specific Heat Ratio*Mach Number^2)*(Pressure Ratio-1)
C_p = 2/(Y*M^2)*(r_p-1)

What is a blast wave?

In fluid dynamics, a blast wave is the increased pressure and flow resulting from the deposition of a large amount of energy in a small, very localised volume.

How to Calculate Pressure Coefficient for Blast Wave Theory?

Pressure Coefficient for Blast Wave Theory calculator uses Pressure Coefficient = 2/(Specific Heat Ratio*Mach Number^2)*(Pressure Ratio-1) to calculate the Pressure Coefficient, The pressure coefficient for blast wave theory formula is defined as the interrelation between specific heat ratio, Mach number at infinity, and pressure ratio. Pressure Coefficient is denoted by C_p symbol.

How to calculate Pressure Coefficient for Blast Wave Theory using this online calculator? To use this online calculator for Pressure Coefficient for Blast Wave Theory, enter Specific Heat Ratio (Y), Mach Number (M) & Pressure Ratio (r_p) and hit the calculate button. Here is how the Pressure Coefficient for Blast Wave Theory calculation can be explained with given input values -> 0.097656 = 2/(1.6*8^2)*(6-1).

FAQ

What is Pressure Coefficient for Blast Wave Theory?

The pressure coefficient for blast wave theory formula is defined as the interrelation between specific heat ratio, Mach number at infinity, and pressure ratio and is represented as C_p = 2/(Y*M^2)*(r_p-1) or Pressure Coefficient = 2/(Specific Heat Ratio*Mach Number^2)*(Pressure Ratio-1). 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, Mach number is a dimensionless quantity representing the ratio of flow velocity past a boundary to the local speed of sound & Pressure Ratio is ratio of final to initial pressure.

How to calculate Pressure Coefficient for Blast Wave Theory?

The pressure coefficient for blast wave theory formula is defined as the interrelation between specific heat ratio, Mach number at infinity, and pressure ratio is calculated using Pressure Coefficient = 2/(Specific Heat Ratio*Mach Number^2)*(Pressure Ratio-1). To calculate Pressure Coefficient for Blast Wave Theory, you need Specific Heat Ratio (Y), Mach Number (M) & Pressure Ratio (r_p). With our tool, you need to enter the respective value for Specific Heat Ratio, Mach Number & Pressure Ratio 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 Pressure Coefficient?

In this formula, Pressure Coefficient uses Specific Heat Ratio, Mach Number & Pressure Ratio. We can use 5 other way(s) to calculate the same, which is/are as follows -

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)
Pressure Coefficient = 0.0137/(Distance from Nose Tip to Required Base Diameter/Length of Shuttle)
Pressure Coefficient = 2/(Specific Heat Ratio*Mach Number^2)*Pressure Ratio

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