Sanjay Krishna
Amrita School of Engineering (ASE), Vallikavu
Sanjay Krishna has created this Calculator and 300+ more calculators!
Rushi Shah
K J Somaiya College of Engineering (K J Somaiya), Mumbai
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11 Other formulas that you can solve using the same Inputs

Allowable Compression Stress when Slenderness Ratio is less than Cc
allowable compression stress=(1-((Slenderness Ratio^2)/(2*Value of Cc^2)))/((5/3)+(3*Slenderness Ratio/(8*Value of Cc))-((Slenderness Ratio^3)/(8*(Value of Cc^3))))*minimum specified yield stress of steel GO
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
Allowable Compression Stress when Slenderness Ratio is Greater than Cc
allowable compression stress=(12*(pi^2)*elastic modulus of steel)/(23*(Slenderness Ratio^2)) GO
Cross-Sectional Area when Critical Buckling Load for Pin Ended Columns is Given
Cross sectional area=Critical Buckling Load*(Slenderness Ratio^2)/((pi^2)*Young's Modulus) 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
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

Coefficient of pressure with slenderness ratio Formula

Pressure coefficient=(2/Specific Heat Ratio*Mach Number^2)*(Non-dimensionalized Pressure*Specific Heat Ratio*(Mach Number^2)*(Slenderness Ratio^2)-1)
C<sub>p</sub>=(2/γ*M^2)*(p-*γ*(M^2)*(λ ^2)-1)
More formulas
Change in velocity for hypersonic flow in x direction GO
Similarity constant equation with slenderness ratio GO
Density ratio with similarity constant having slenderness ratio GO
Non dimensional Change in hypersonic disturbance velocity in x direction GO
Non dimensional Change in hypersonic disturbance velocity in y direction GO
Non dimensional pressure equation with slenderness ratio GO
Non dimensional Velocity disturbance in y direction in hypersonic flow GO
Coefficient of pressure with slenderness ratio and similarity constant GO
Similarity constant equation using the wave angle GO
Rasmussen closed-form expression for the shock-wave angle GO
Doty and Rasmussen - normal-force coefficient GO
Inverse of density for hypersonic flow GO
Inverse of density for hypersonic flow using mach number GO
Constant g used for finding the location of perturbed shock GO
Non- dimensionalised time GO
Distance from tip of the leading edge to the base GO

What is pressure coefficient?

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

How to Calculate Coefficient of pressure with slenderness ratio?

Coefficient of pressure with slenderness ratio calculator uses Pressure coefficient=(2/Specific Heat Ratio*Mach Number^2)*(Non-dimensionalized Pressure*Specific Heat Ratio*(Mach Number^2)*(Slenderness Ratio^2)-1) to calculate the Pressure coefficient, The Coefficient of pressure with slenderness ratio formula is defined as the interrelation between the specific heat ratio, non dimensional pressure, Mach infinity and slenderness ratio. Pressure coefficient and is denoted by Cp symbol.

How to calculate Coefficient of pressure with slenderness ratio using this online calculator? To use this online calculator for Coefficient of pressure with slenderness ratio, enter Specific Heat Ratio (γ), Mach Number (M), Non-dimensionalized Pressure (p-) and Slenderness Ratio (λ ) and hit the calculate button. Here is how the Coefficient of pressure with slenderness ratio calculation can be explained with given input values -> 4998.75 = (2/1.6*1^2)*(1*1.6*(1^2)*(50^2)-1).

FAQ

What is Coefficient of pressure with slenderness ratio?
The Coefficient of pressure with slenderness ratio formula is defined as the interrelation between the specific heat ratio, non dimensional pressure, Mach infinity and slenderness ratio and is represented as Cp=(2/γ*M^2)*(p-*γ*(M^2)*(λ ^2)-1) or Pressure coefficient=(2/Specific Heat Ratio*Mach Number^2)*(Non-dimensionalized Pressure*Specific Heat Ratio*(Mach Number^2)*(Slenderness Ratio^2)-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, Non-dimensionalized Pressure is the technique can ease the analysis of the problem at hand, and reduce the number of free parameters and The Slenderness ratio is the ratio of the length of a column and the least radius of gyration of its cross section.
How to calculate Coefficient of pressure with slenderness ratio?
The Coefficient of pressure with slenderness ratio formula is defined as the interrelation between the specific heat ratio, non dimensional pressure, Mach infinity and slenderness ratio is calculated using Pressure coefficient=(2/Specific Heat Ratio*Mach Number^2)*(Non-dimensionalized Pressure*Specific Heat Ratio*(Mach Number^2)*(Slenderness Ratio^2)-1). To calculate Coefficient of pressure with slenderness ratio, you need Specific Heat Ratio (γ), Mach Number (M), Non-dimensionalized Pressure (p-) and Slenderness Ratio (λ ). With our tool, you need to enter the respective value for Specific Heat Ratio, Mach Number, Non-dimensionalized Pressure and Slenderness 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, Non-dimensionalized Pressure and Slenderness 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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