Power required for given aerodynamic coefficients Calculator

Category	Physics ↺
Physics	Flight Stability and Control ↺
Flight-Stability-And-Control	Airplane Performance ↺
Airplane-Performance	Power Required for Level Unaccelerated Flight ↺

✖Weight is a vector quantity and defined as the product of mass and acceleration acting on that massⓘ Weight [W]			+10% -10%
✖The Freestream Velocity is the velocity of air far upstream of an aerodynamic body, that is before the body has a chance to deflect, slow down or compress the airⓘ Freestream Velocity [V_∞]			+10% -10%
✖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%
✖The lift coefficient (CL) is a dimensionless coefficient that relates the lift generated by a lifting body to the fluid density around the body, the fluid velocity and an associated reference area. ⓘ lift coefficient [C_L]			+10% -10%

✖Power is the amount of energy liberated per second in a device.ⓘ Power required for given aerodynamic coefficients [P]

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Vinay Mishra

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

Vinay Mishra has created this Calculator and 300+ more calculators!

Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

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

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

Drag Coefficient for given zero-lift drag coefficient

Drag Coefficient=Zero-lift drag coefficient+((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)) GO

Drag Coefficient for given parasite drag coefficient

Drag Coefficient=Parasite Drag coefficient+((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)) GO

Coefficient of Drag due to lift

Coefficient of drag due to lift=(lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing) GO

Parasite Drag Coefficient at zero lift

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

Lift for an unaccelerated flight

Lift force=Weight-(Thrust of an aircraft*sin(Thrust angle)) GO

Thrust angle for an unaccelerated flight for given lift

Thrust angle=asin((Weight-Lift force)/Thrust of an aircraft) GO

Thrust required for level, unaccelerated flight

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

Dynamic pressure based on coefficient of lift

Dynamic Pressure=Lift force/(lift coefficient*Area) GO

Dynamic pressure

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

Lift Force

Lift force=lift coefficient*Dynamic Pressure*Area GO

Drag force

Drag Force=Drag Coefficient*Dynamic Pressure*Area GO

< 11 Other formulas that calculate the same Output

Power transmittted by a belt

Power=(Tensions in the tight side of belt-Tensions in the slack side of belt)* Velocity of the belt GO

Power In Single-Phase AC Circuits When Current Is Given

Power=Electric Current*Electric Current*Resistance*cos(Theta) GO

Power when electric potential difference and electric current are given

Power=Electric Potential Difference*Electric Current GO

Power, when electric potential difference and resistance are given,

Power=Electric Potential Difference^2/Resistance GO

Power In Single-Phase AC Circuits

Power=Voltage*Electric Current*cos(Theta) GO

Power Generated When The Armature Current Is Given

Power=Induced voltage*Armature Current GO

Converted Power

Power=Induced voltage*Armature Current GO

Power, when electric current and resistance are given

Power=(Electric Current)^2*Resistance GO

Power Generated When Torque is Given

Power=Angular Speed*Torque GO

Gross Mechanical Power

Power=(1-Slip)*Input Power GO

Output Power

Power=Voltage*Load current GO

Power required for given aerodynamic coefficients Formula

Power=Weight*Freestream Velocity*Drag Coefficient/lift coefficient
P=W*V∞*CD/CL

More formulas

Power required for given required thrust GO

Thrust required for given required power GO

Freestream velocity for given required power GO

Weight of aircraft for given required power GO

Zero-lift drag coefficient for minimum power required GO

Coefficient of Drag due to lift for minimum power required GO

Power required for given total drag GO

Total drag for given required power GO

Freestream Velocity for given total drag GO

What are aerodynamic coefficients?

Aerodynamic Coefficients are dimensionless quantities that characterize the aerodynamic force and moment acting on an object moving through a fluid or gaseous medium.

How to Calculate Power required for given aerodynamic coefficients?

Power required for given aerodynamic coefficients calculator uses Power=Weight*Freestream Velocity*Drag Coefficient/lift coefficient to calculate the Power, The Power required for given aerodynamic coefficients in a steady, level flight is a function of the weight and freestream velocity of the aircraft. Power and is denoted by P symbol.

How to calculate Power required for given aerodynamic coefficients using this online calculator? To use this online calculator for Power required for given aerodynamic coefficients, enter Weight (W), Freestream Velocity (V_∞), Drag Coefficient (C_D) and lift coefficient (C_L) and hit the calculate button. Here is how the Power required for given aerodynamic coefficients calculation can be explained with given input values -> 100000 = 100*100*100/10.

FAQ

What is Power required for given aerodynamic coefficients?

The Power required for given aerodynamic coefficients in a steady, level flight is a function of the weight and freestream velocity of the aircraft and is represented as P=W*V_∞*C_D/C_L or Power=Weight*Freestream Velocity*Drag Coefficient/lift coefficient. Weight is a vector quantity and defined as the product of mass and acceleration acting on that mass, The Freestream Velocity is the velocity of air far upstream of an aerodynamic body, that is before the body has a chance to deflect, slow down or compress the air, 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 and The lift coefficient (CL) is a dimensionless coefficient that relates the lift generated by a lifting body to the fluid density around the body, the fluid velocity and an associated reference area. .

How to calculate Power required for given aerodynamic coefficients?

The Power required for given aerodynamic coefficients in a steady, level flight is a function of the weight and freestream velocity of the aircraft is calculated using Power=Weight*Freestream Velocity*Drag Coefficient/lift coefficient. To calculate Power required for given aerodynamic coefficients, you need Weight (W), Freestream Velocity (V_∞), Drag Coefficient (C_D) and lift coefficient (C_L). With our tool, you need to enter the respective value for Weight, Freestream Velocity, Drag Coefficient and lift coefficient 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 Power?

In this formula, Power uses Weight, Freestream Velocity, Drag Coefficient and lift coefficient. We can use 11 other way(s) to calculate the same, which is/are as follows -

Power=Electric Potential Difference*Electric Current
Power=(Electric Current)^2*Resistance
Power=Electric Potential Difference^2/Resistance
Power=(1-Slip)*Input Power
Power=Angular Speed*Torque
Power=Induced voltage*Armature Current
Power=Voltage*Load current
Power=Induced voltage*Armature Current
Power=(Tensions in the tight side of belt-Tensions in the slack side of belt)* Velocity of the belt
Power=Voltage*Electric Current*cos(Theta)
Power=Electric Current*Electric Current*Resistance*cos(Theta)

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