Pressure coefficient for Blunt-nosed plate: Calculator

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✖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ⓘ Drag Coefficient [C_D]			+10% -10%
✖Distance from Y-axis is defined as the distance from the point where stress is to be computed to the YY axis.ⓘ Distance from Y-axis [x]			+10% -10%
✖The diameter one is at the larger sideⓘ diameter one [d1]			+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 Blunt-nosed plate: [C_p]

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Pressure coefficient for Blunt-nosed plate:

Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

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

Vinay Mishra

Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune

Vinay Mishra has verified this Calculator and 100+ more calculators!

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

Parasite Drag Coefficient at zero lift

Zero-lift drag coefficient=Drag Coefficient-Coefficient of drag due to lift GO

Power required for given aerodynamic coefficients

Power=Weight*Freestream Velocity*Drag Coefficient/lift coefficient GO

Weight of aircraft for given coefficients of lift and drag

Weight=lift coefficient*Thrust of an aircraft/Drag Coefficient GO

Coefficient of Lift for given thrust and weight

lift coefficient=Weight*Drag Coefficient/Thrust of an aircraft GO

Thrust for given coefficients of lift and drag

Thrust of an aircraft=Drag Coefficient*Weight/lift coefficient GO

Thrust required for level, unaccelerated flight

Thrust of an aircraft=Dynamic Pressure*Area*Drag Coefficient GO

Coefficient of Lift for given thrust-to-weight ratio

lift coefficient=Drag Coefficient/Thrust-to-weight ratio GO

Thrust-to-weight ratio

Thrust-to-weight ratio=Drag Coefficient/lift coefficient GO

Dynamic pressure

Dynamic Pressure=Drag Force/(Drag Coefficient*Area) GO

Drag for a level, unaccelerated flight at negligible thrust angle

Drag Force=Dynamic Pressure*Area*Drag Coefficient GO

Drag force

Drag Force=Drag Coefficient*Dynamic Pressure*Area 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 for Blunt-nosed plate: Formula

Pressure coefficient=0.173*(Drag Coefficient^(2/3))/((Distance from Y-axis/diameter one)^(2/3))
C<sub>p</sub>=0.173*(C<sub>D</sub>^(2/3))/((x/d1)^(2/3))

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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 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 coefficient of drag?

The drag coefficient is a number that aerodynamicists use to model all of the complex dependencies of shape, inclination, and flow conditions on aircraft drag

How to Calculate Pressure coefficient for Blunt-nosed plate:?

Pressure coefficient for Blunt-nosed plate: calculator uses Pressure coefficient=0.173*(Drag Coefficient^(2/3))/((Distance from Y-axis/diameter one)^(2/3)) to calculate the Pressure coefficient, The Pressure coefficient for Blunt-nosed plate: formula is defined as the inter relation between drag coefficient, distance from the tip of the blunt nose and base diameter, since its an axis symmetric body the distance is taken along the x axis, where tip of the body is origin. Pressure coefficient and is denoted by C_p symbol.

How to calculate Pressure coefficient for Blunt-nosed plate: using this online calculator? To use this online calculator for Pressure coefficient for Blunt-nosed plate:, enter Drag Coefficient (C_D), Distance from Y-axis (x) and diameter one (d1) and hit the calculate button. Here is how the Pressure coefficient for Blunt-nosed plate: calculation can be explained with given input values -> 0.318669 = 0.173*(100^(2/3))/((0.04/0.001)^(2/3)).

FAQ

What is Pressure coefficient for Blunt-nosed plate:?

The Pressure coefficient for Blunt-nosed plate: formula is defined as the inter relation between drag coefficient, distance from the tip of the blunt nose and base diameter, since its an axis symmetric body the distance is taken along the x axis, where tip of the body is origin and is represented as C_p=0.173*(C_D^(2/3))/((x/d1)^(2/3)) or Pressure coefficient=0.173*(Drag Coefficient^(2/3))/((Distance from Y-axis/diameter one)^(2/3)). 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 Y-axis is defined as the distance from the point where stress is to be computed to the YY axis and The diameter one is at the larger side.

How to calculate Pressure coefficient for Blunt-nosed plate:?

The Pressure coefficient for Blunt-nosed plate: formula is defined as the inter relation between drag coefficient, distance from the tip of the blunt nose and base diameter, since its an axis symmetric body the distance is taken along the x axis, where tip of the body is origin is calculated using Pressure coefficient=0.173*(Drag Coefficient^(2/3))/((Distance from Y-axis/diameter one)^(2/3)). To calculate Pressure coefficient for Blunt-nosed plate:, you need Drag Coefficient (C_D), Distance from Y-axis (x) and diameter one (d1). With our tool, you need to enter the respective value for Drag Coefficient, Distance from Y-axis and diameter one 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 Drag Coefficient, Distance from Y-axis and diameter one. 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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