Sanjay Krishna
Amrita School of Engineering (ASE), Vallikavu
Sanjay Krishna has created this Calculator and 300+ more calculators!
Maiarutselvan V
PSG College of Technology (PSGCT), Coimbatore
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11 Other formulas that you can solve using the same Inputs

Heat Loss due to Pipe
Heat Loss due to Pipe=(Force*Length*Fluid Velocity^2)/(2*Diameter *Acceleration Due To Gravity) GO
Reynolds Number for Circular Tubes
Reynolds Number=Density*Fluid Velocity*Diameter /Dynamic viscosity GO
Perimeter of a Semicircle when circumference of circle is given
Perimeter=(Circumference of Circle/2)+Diameter GO
Diameter of circumscribing sphere when diameter and height of circumscribed cylinder is known
Diameter of Sphere=sqrt(Diameter ^2+Height^2) GO
Cutting Speed
Cutting Speed=pi*Diameter *Angular Speed GO
Area of a Circle when diameter is given
Area of Circle=(pi/4)*Diameter ^2 GO
Perimeter of a quarter circle when diameter is given
Perimeter=Diameter *((pi/4)+1) GO
Perimeter of a Semicircle when diameter is given
Perimeter=Diameter *((pi/2)+1) GO
Area of a quarter circle when diameter is given
Area=(pi*(Diameter )^2)/16 GO
Area of a Semicircle when diameter is given
Area=(pi*(Diameter )^2)/8 GO
Radius of a circle when diameter is given
Radius=Diameter /2 GO

11 Other formulas that calculate the same Output

Pressure ratio for unsteady waves with subtracted induced mass motion for expansion waves
pressure ratio=(1-((Specific Heat Ratio-1)/2)*(Induced mass motion/Speed of Sound))^(2*Specific Heat Ratio/(Specific Heat Ratio-1)) GO
Pressure ratio for unsteady waves
pressure ratio=(1+((Specific Heat Ratio-1)/2)*(Induced mass motion/Speed of Sound))^(2*Specific Heat Ratio/(Specific Heat Ratio-1)) GO
Pressure ratio having high mach number with similarity constant
pressure ratio=(1-((Specific Heat Ratio-1)/2)*Hypersonic similarity parameter)^(2*Specific Heat Ratio/(Specific Heat Ratio-1)) GO
Pressure ratio for high Mach number
pressure ratio=(Mach Number ahead of shock/Mach Number behind shock)^(2*Specific Heat Ratio/(Specific Heat Ratio-1)) GO
Pressure ratio for blunt cylinder blast wave
pressure ratio=0.8773*[BoltZ]*(Mach Number^2)*(sqrt(Drag Coefficient))*(Distance from X-axis/Diameter ^(-1)) GO
Pressure ratio for blunt slab blast wave
pressure ratio=0.127*(Mach Number^2)*(Drag Coefficient^(2/3))*((Distance from X-axis/Diameter )^(-2/3)) GO
Exact pressure ratio
pressure ratio=1+(2*Specific Heat Ratio/(Specific Heat Ratio+1))*(((Mach Number*sin(Wave angle))^2)-1) GO
Blunt-nosed flat plate pressure ratio (first approximation)
pressure ratio=0.121*(Mach Number^2)*((Drag Coefficient/(Distance from X-axis/Diameter ))^(2/3)) GO
Pressure ratio when Mach becomes infinite
pressure ratio=(2*Specific Heat Ratio/(Specific Heat Ratio+1))*((Mach Number*sin(Wave angle))^2) GO
Simplified pressure ratio for blunt cylinder blast wave
pressure ratio=0.0681*(Mach Number^2)*sqrt(Drag Coefficient)/(Distance from X-axis/Diameter ) GO
Pressure ratio
pressure ratio=Final Pressure of System/Initial Pressure of System GO

Pressure ratio of Blunt-nosed cylinder (first approximation): Formula

pressure ratio=0.067*(Mach Number^2)*sqrt(Drag Coefficient)/(Distance from X-axis/Diameter )
Rp=0.067*(M^2)*sqrt(C<sub>D</sub>)/(y/d)
More formulas
Forces acting on body along the flight path GO
Forces acting Perpendicular to the body on the flight path GO
Blunt-nosed radial coordinate flat plate (first approximation): GO
Radial coordinate of Blunt-nosed cylinder (first approximation): GO
Radius of curvature for the sphere-cone body shape GO
Radius of curvature for the cylinder-wedge GO
Radius for the sphere-cone body shape GO
Radius for the cylinder-wedge body shape GO

What is 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 ratio of Blunt-nosed cylinder (first approximation):?

Pressure ratio of Blunt-nosed cylinder (first approximation): calculator uses pressure ratio=0.067*(Mach Number^2)*sqrt(Drag Coefficient)/(Distance from X-axis/Diameter ) to calculate the pressure ratio, Pressure ratio of Blunt-nosed cylinder (first approximation): formula is defined as interrelation between drag coefficient, mach number at infinity, distance from the tip of the slab and base diameter. pressure ratio and is denoted by Rp symbol.

How to calculate Pressure ratio of Blunt-nosed cylinder (first approximation): using this online calculator? To use this online calculator for Pressure ratio of Blunt-nosed cylinder (first approximation):, enter Mach Number (M), Drag Coefficient (CD), Distance from X-axis (y) and Diameter (d) and hit the calculate button. Here is how the Pressure ratio of Blunt-nosed cylinder (first approximation): calculation can be explained with given input values -> 670 = 0.067*(1^2)*sqrt(100)/(0.01/10).

FAQ

What is Pressure ratio of Blunt-nosed cylinder (first approximation):?
Pressure ratio of Blunt-nosed cylinder (first approximation): formula is defined as interrelation between drag coefficient, mach number at infinity, distance from the tip of the slab and base diameter and is represented as Rp=0.067*(M^2)*sqrt(CD)/(y/d) or pressure ratio=0.067*(Mach Number^2)*sqrt(Drag Coefficient)/(Distance from X-axis/Diameter ). Mach number is a dimensionless quantity representing the ratio of flow velocity past a boundary to the local speed of sound, Drag Coefficient is a dimensionless quantity that is used to quantify the drag or resistance of an object in a fluid environment, such as air or water, Distance from X-axis is defined as the distance from the point where stress is to be computed to XX axis and Diameter is a straight line passing from side to side through the center of a body or figure, especially a circle or sphere.
How to calculate Pressure ratio of Blunt-nosed cylinder (first approximation):?
Pressure ratio of Blunt-nosed cylinder (first approximation): formula is defined as interrelation between drag coefficient, mach number at infinity, distance from the tip of the slab and base diameter is calculated using pressure ratio=0.067*(Mach Number^2)*sqrt(Drag Coefficient)/(Distance from X-axis/Diameter ). To calculate Pressure ratio of Blunt-nosed cylinder (first approximation):, you need Mach Number (M), Drag Coefficient (CD), Distance from X-axis (y) and Diameter (d). With our tool, you need to enter the respective value for Mach Number, Drag Coefficient, Distance from X-axis and Diameter 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 ratio?
In this formula, pressure ratio uses Mach Number, Drag Coefficient, Distance from X-axis and Diameter . We can use 11 other way(s) to calculate the same, which is/are as follows -
  • pressure ratio=1+(2*Specific Heat Ratio/(Specific Heat Ratio+1))*(((Mach Number*sin(Wave angle))^2)-1)
  • pressure ratio=(2*Specific Heat Ratio/(Specific Heat Ratio+1))*((Mach Number*sin(Wave angle))^2)
  • pressure ratio=(Mach Number ahead of shock/Mach Number behind shock)^(2*Specific Heat Ratio/(Specific Heat Ratio-1))
  • pressure ratio=(1-((Specific Heat Ratio-1)/2)*Hypersonic similarity parameter)^(2*Specific Heat Ratio/(Specific Heat Ratio-1))
  • pressure ratio=Final Pressure of System/Initial Pressure of System
  • pressure ratio=0.8773*[BoltZ]*(Mach Number^2)*(sqrt(Drag Coefficient))*(Distance from X-axis/Diameter ^(-1))
  • pressure ratio=0.0681*(Mach Number^2)*sqrt(Drag Coefficient)/(Distance from X-axis/Diameter )
  • pressure ratio=0.127*(Mach Number^2)*(Drag Coefficient^(2/3))*((Distance from X-axis/Diameter )^(-2/3))
  • pressure ratio=0.121*(Mach Number^2)*((Drag Coefficient/(Distance from X-axis/Diameter ))^(2/3))
  • pressure ratio=(1+((Specific Heat Ratio-1)/2)*(Induced mass motion/Speed of Sound))^(2*Specific Heat Ratio/(Specific Heat Ratio-1))
  • pressure ratio=(1-((Specific Heat Ratio-1)/2)*(Induced mass motion/Speed of Sound))^(2*Specific Heat Ratio/(Specific Heat Ratio-1))
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