Exact pressure coefficient for blast wave theory Calculator

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✖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 [γ]			+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 [Rp]			+10% -10%

✖Pressure coefficient defines the value of local pressure at a point in terms of free stream pressure and dynamic pressure.ⓘ Exact pressure coefficient for blast wave theory [C_p]

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Exact pressure coefficient for blast wave theory

Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

Sanjay Krishna has created this Calculator and 200+ more calculators!

Maiarutselvan V

PSG College of Technology (PSGCT), Coimbatore

Maiarutselvan V has verified this Calculator and 200+ more calculators!

< 11 Other formulas that you can solve using the same Inputs

Ratio of stagnation and static pressure

Stagnation to Static Pressure=(1+(((Specific Heat Ratio-1)/2)*(Mach Number^2)))^(Specific Heat Ratio/(Specific Heat Ratio-1)) GO

Ratio of Stagnation and Static Density

Stagnation to Static Density=(1+(((Specific Heat Ratio-1)/2)*(Mach Number^2)))^(1/(Specific Heat Ratio-1)) GO

Deflection angle

deflection angle=(2/(Specific Heat Ratio-1))*((1/Mach Number ahead of shock)-(1/Mach Number behind shock)) GO

Relation between Characteristic Mach number and Mach number

Characteristic Mach number=((Specific heat ratio+1)/((Specific heat ratio-1)+(2/(Mach Number^2))))^0.5 GO

Exact pressure ratio

pressure ratio=1+(2*Specific Heat Ratio/(Specific Heat Ratio+1))*(((Mach Number*sin(Wave angle))^2)-1) GO

Volumetric Efficiency

volumetric efficiency=1+compression ratio+(compression ratio)* ((pressure ratio)^(1/gamma)) GO

Mach number

Mach Number=Fluid Velocity/(sqrt(Specific Heat Ratio*Universal Gas Constant*final temp.)) GO

Ratio of Stagnation and Static Temperature

Stagnation to Static Temperature=1+(((Specific Heat Ratio-1)/2)*(Mach Number^2)) GO

Brayton Cycle Efficiency

thermal efficiency of brayton cycle=1-1/(pressure ratio^((gamma-1)/gamma)) GO

Speed of Sound

Speed of Sound=sqrt(Specific Heat Ratio*[R-Dry-Air]*Temperature of Gas) GO

Mach Angle

Mach Angle=asin(1/Mach Number) GO

< 11 Other formulas that calculate the same Output

Coefficient of pressure with similarity parameters

Pressure coefficient=(2*(Flow Deflection angle)^2)*(((Specific Heat Ratio+1)/4)+sqrt((((Specific Heat Ratio+1)/4)^2)+(1/(Hypersonic similarity parameter)^2))) GO

Coefficient of pressure with slenderness ratio

Pressure coefficient=2*(Slenderness Ratio^2)*(Non-dimensionalized Pressure-(1/(Specific Heat Ratio*(Mach Number^2)*(Slenderness Ratio^2)))) GO

Pressure coefficient for slender bodies of revolution

Pressure coefficient=2*(Angle of Deflection^2)+(Curvature of the surface *Distance of Point from Centroidal Axis) GO

Pressure coefficient for slender 2-D bodies

Pressure coefficient=2*((deflection angle^2)+(Curvature of the surface *Distance of Point from Centroidal Axis)) GO

Exact relation for pressure coefficient behind an oblique shock wave

Pressure coefficient=(4/(Specific Heat Ratio+1))*(((sin(Wave angle))^2)-(1/Mach Number^2)) GO

Modified Newtonian Law

Pressure coefficient=The maximum pressure coefficient*(sin(deflection angle))^2 GO

Exact relation for pressure coefficient behind an oblique shock wave when Mach no. tends to infinite

Pressure coefficient=(4/(Specific Heat Ratio+1))*(sin(Wave angle))^2 GO

Supersonic expression for pressure coefficient on a surface with local deflection angle θ

Pressure coefficient=(2*deflection angle)/(sqrt(Mach Number^2-1)) GO

Non-dimensional pressure coefficient

Pressure coefficient=Change in static pressure/Dynamic Pressure GO

Newtonian sine-squared law for pressure coefficient

Pressure coefficient=2*(sin(deflection angle))^2 GO

Coefficient of pressure derived from oblique shock theory

Pressure coefficient=2*(sin(Wave angle))^2 GO

Exact pressure coefficient for blast wave theory Formula

Pressure coefficient=(2/(Specific Heat Ratio*Mach Number^2))*(pressure ratio-1)
C<sub>p</sub>=(2/(γ*M^2))*(Rp-1)

More formulas

Pressure coefficient for blast wave theory at very high values of mach GO

Pressure coefficient for Blunt-nosed plate: GO

Pressure coefficient for Blunt-nosed cylinder: GO

Pressure coefficient combined with blast wave for the shuttle GO

Pressure coefficient combined with blast wave for the shuttle at angle of attack GO

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 Exact pressure coefficient for blast wave theory?

Exact 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 Exact 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 and is denoted by C_p symbol.

How to calculate Exact pressure coefficient for blast wave theory using this online calculator? To use this online calculator for Exact pressure coefficient for blast wave theory, enter Specific Heat Ratio (γ), Mach Number (M) and pressure ratio (Rp) and hit the calculate button. Here is how the Exact pressure coefficient for blast wave theory calculation can be explained with given input values -> 1.25 = (2/(1.6*1^2))*(2-1).

FAQ

What is Exact pressure coefficient for blast wave theory?

The Exact 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/(γ*M^2))*(Rp-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 and pressure ratio is ratio of final to initial pressure.

How to calculate Exact pressure coefficient for blast wave theory?

The Exact 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 Exact pressure coefficient for blast wave theory, you need Specific Heat Ratio (γ), Mach Number (M) and pressure ratio (Rp). With our tool, you need to enter the respective value for Specific Heat Ratio, Mach Number and 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 and pressure ratio. We can use 11 other way(s) to calculate the same, which is/are as follows -

Pressure coefficient=Change in static pressure/Dynamic Pressure
Pressure coefficient=(4/(Specific Heat Ratio+1))*(((sin(Wave angle))^2)-(1/Mach Number^2))
Pressure coefficient=(4/(Specific Heat Ratio+1))*(sin(Wave angle))^2
Pressure coefficient=(2*(Flow Deflection angle)^2)*(((Specific Heat Ratio+1)/4)+sqrt((((Specific Heat Ratio+1)/4)^2)+(1/(Hypersonic similarity parameter)^2)))
Pressure coefficient=2*(sin(deflection angle))^2
Pressure coefficient=(2*deflection angle)/(sqrt(Mach Number^2-1))
Pressure coefficient=The maximum pressure coefficient*(sin(deflection angle))^2
Pressure coefficient=2*((deflection angle^2)+(Curvature of the surface *Distance of Point from Centroidal Axis))
Pressure coefficient=2*(Angle of Deflection^2)+(Curvature of the surface *Distance of Point from Centroidal Axis)
Pressure coefficient=2*(sin(Wave angle))^2
Pressure coefficient=2*(Slenderness Ratio^2)*(Non-dimensionalized Pressure-(1/(Specific Heat Ratio*(Mach Number^2)*(Slenderness Ratio^2))))

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