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Pressure coefficient combined with blast wave for the shuttle Calculator

Category Engineering ↺
Engineering Mechanical ↺
Mechanical Fluid Mechanics ↺
Fluid-Mechanics Hypersonic Flow ↺
Hypersonic-Flow Blast-wave part 2 ↺
✖Distance from the nose tip to required base dia, used for studying the leading edge of the hypersonic vehiclesⓘ Distance from the nose tip to required base dia [x]
+10%
-10%
✖Length of the shuttle variable is used for studying the coefficient of pressureⓘ Length of the shuttle [l]
+10%
-10%
✖Pressure coefficient defines the value of local pressure at a point in terms of free stream pressure and dynamic pressure.ⓘ Pressure coefficient combined with blast wave for the shuttle [Cp]
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Sanjay Krishna
Amrita School of Engineering (ASE), Vallikavu
Sanjay Krishna has created this Calculator and 300+ more calculators!
Shikha Maurya
Indian Institute of Technology (IIT), Bombay
Shikha Maurya has verified this Calculator and 100+ more calculators!

5 Other formulas that you can solve using the same Inputs

Nusselt number for hypersonic vehicle
Nusselt Number=((Local heat transfer rate*Distance from the nose tip to required base dia))/(Thermal Conductivity*(Adiabatic wall temperature-Wall temperature)) GO
Thermal conductivity at the edge of the boundary layer equation using Nusselt's number
Thermal Conductivity=(Local heat transfer rate*Distance from the nose tip to required base dia)/(Nusselt Number*(Adiabatic wall temperature-Wall temperature)) GO
local heat-transfer rate using Nusselt's number
Local heat transfer rate=(Nusselt Number*Thermal Conductivity*(Adiabatic wall temperature-Wall temperature))/(Distance from the nose tip to required base dia) GO
Pressure coefficient for Blunt-nosed cylinder:
Pressure coefficient=0.096*(Drag Coefficient^(1/2))/(Distance from the nose tip to required base dia/Diameter ) GO
Pressure coefficient combined with blast wave for the shuttle at angle of attack
Pressure coefficient=(0.0137/(Distance from X-axis/Length of the shuttle))+2*(sin(Angle of attack))^2 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

Pressure coefficient combined with blast wave for the shuttle Formula

Pressure coefficient=0.0137/(Distance from the nose tip to required base dia/Length of the shuttle)
C<sub>p</sub>=0.0137/(x/l)
More formulas
Exact pressure coefficient for blast wave theory GO
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 at angle of attack GO

What is pressure coefficient?

The pressure coefficient is a dimensionless number which describes the relative pressures throughout a flow field in fluid dynamics.

How to Calculate Pressure coefficient combined with blast wave for the shuttle?

Pressure coefficient combined with blast wave for the shuttle calculator uses Pressure coefficient=0.0137/(Distance from the nose tip to required base dia/Length of the shuttle) to calculate the Pressure coefficient, The Pressure coefficient combined with blast wave for the shuttle formula is defined as the inverse of ratio of distance from the tip pf shuttle to the length of the shuttle. Pressure coefficient and is denoted by Cp symbol.

How to calculate Pressure coefficient combined with blast wave for the shuttle using this online calculator? To use this online calculator for Pressure coefficient combined with blast wave for the shuttle, enter Distance from the nose tip to required base dia (x) and Length of the shuttle (l) and hit the calculate button. Here is how the Pressure coefficient combined with blast wave for the shuttle calculation can be explained with given input values -> 0.0137 = 0.0137/(10/10).

FAQ

What is Pressure coefficient combined with blast wave for the shuttle?
The Pressure coefficient combined with blast wave for the shuttle formula is defined as the inverse of ratio of distance from the tip pf shuttle to the length of the shuttle and is represented as Cp=0.0137/(x/l) or Pressure coefficient=0.0137/(Distance from the nose tip to required base dia/Length of the shuttle). Distance from the nose tip to required base dia, used for studying the leading edge of the hypersonic vehicles and Length of the shuttle variable is used for studying the coefficient of pressure.
How to calculate Pressure coefficient combined with blast wave for the shuttle?
The Pressure coefficient combined with blast wave for the shuttle formula is defined as the inverse of ratio of distance from the tip pf shuttle to the length of the shuttle is calculated using Pressure coefficient=0.0137/(Distance from the nose tip to required base dia/Length of the shuttle). To calculate Pressure coefficient combined with blast wave for the shuttle, you need Distance from the nose tip to required base dia (x) and Length of the shuttle (l). With our tool, you need to enter the respective value for Distance from the nose tip to required base dia and Length of the shuttle 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 Distance from the nose tip to required base dia and Length of the shuttle. 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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