Power required for given aerodynamic coefficients Calculator

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Thrust and Power Requirements

Lift and Drag Requirements

✖Weight of Body is the force acting on the object due to gravity.ⓘ Weight of Body [W_body]			+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 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 defined as the product of thrust force and velocity of aircraft.ⓘ Power required for given aerodynamic coefficients [P]

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Formula

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Power required for given aerodynamic coefficients

Formula

`"P" = "W"_{"body"}*"V"_{"∞"}*"C"_{"D"}/"C"_{"L"}`

Example

`"3013.636W"="221N"*"30m/s"*"0.5"/"1.1"`

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Power required for given aerodynamic coefficients Solution

STEP 0: Pre-Calculation Summary

Formula Used

Power = Weight of Body*Freestream Velocity*Drag Coefficient/Lift Coefficient
P = W_body*V_∞*C_D/C_L
This formula uses 5 Variables

Variables Used

Power - (Measured in Watt) - Power is defined as the product of thrust force and velocity of aircraft.
Weight of Body - (Measured in Newton) - Weight of Body is the force acting on the object due to gravity.
Freestream Velocity - (Measured in Meter per Second) - 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 - 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.
Lift Coefficient - The Lift Coefficient 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.

STEP 1: Convert Input(s) to Base Unit

Weight of Body: 221 Newton --> 221 Newton No Conversion Required
Freestream Velocity: 30 Meter per Second --> 30 Meter per Second No Conversion Required
Drag Coefficient: 0.5 --> No Conversion Required
Lift Coefficient: 1.1 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

P = W_body*V_∞*C_D/C_L --> 221*30*0.5/1.1

Evaluating ... ...

P = 3013.63636363636

STEP 3: Convert Result to Output's Unit

3013.63636363636 Watt --> No Conversion Required

FINAL ANSWER

3013.63636363636 ≈ 3013.636 Watt <-- Power

(Calculation completed in 00.004 seconds)

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Created by Vinay Mishra

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

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Verified by Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

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< 19 Thrust and Power Requirements Calculators

Minimum Thrust required for given weight

Go Thrust = (Dynamic Pressure*Area*Zero Lift Drag Coefficient)+((Weight of Body^2)/(Dynamic Pressure*Area*pi*Oswald Efficiency Factor*Aspect Ratio of a wing))

Minimum Thrust required for given lift coefficient

Go Thrust = Dynamic Pressure*Area*(Zero Lift Drag Coefficient+((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing)))

Minimum Thrust of aircraft required

Go Thrust = Dynamic Pressure*Reference Area*(Zero Lift Drag Coefficient+Coefficient Of Drag Due to Lift)

Weight of aircraft for given required power

Go Weight of Body = Power*Lift Coefficient/(Freestream Velocity*Drag Coefficient)

Power required for given aerodynamic coefficients

Go Power = Weight of Body*Freestream Velocity*Drag Coefficient/Lift Coefficient

Thrust Angle for Unaccelerated Level Flight for given Lift

Go Thrust angle = asin((Weight of Body-Lift Force)/Thrust)

Weight of aircraft in level, unaccelerated flight

Go Weight of Body = Lift Force+(Thrust*sin(Thrust angle))

Weight of aircraft for given coefficients of lift and drag

Go Weight of Body = Lift Coefficient*Thrust/Drag Coefficient

Thrust for given coefficients of lift and drag

Go Thrust = Drag Coefficient*Weight of Body/Lift Coefficient

Weight of aircraft for level, unaccelerated flight at negligible thrust angle

Go Weight of Body = Dynamic Pressure*Area*Lift Coefficient

Thrust of aircraft required for level, unaccelerated flight

Go Thrust = Dynamic Pressure*Area*Drag Coefficient

Thrust for Level and Unaccelerated Flight

Go Thrust = Drag Force/(cos(Thrust angle))

Thrust Angle for Unaccelerated Level Flight for given Drag

Go Thrust angle = acos(Drag Force/Thrust)

Thrust-to-weight ratio

Go Thrust-to-Weight Ratio = Drag Coefficient/Lift Coefficient

Thrust of aircraft required for given Lift-to-drag ratio

Go Thrust = Weight of Body/Lift-to-drag Ratio

Weight of aircraft for given Lift-to-drag ratio

Go Weight of Body = Thrust*Lift-to-drag Ratio

Power required for given total drag force

Go Power = Drag Force*Freestream Velocity

Power required for given required thrust of aircraft

Go Power = Freestream Velocity*Thrust

Thrust of aircraft required for given required power

Go Thrust = Power/Freestream Velocity

Power required for given aerodynamic coefficients Formula

Power = Weight of Body*Freestream Velocity*Drag Coefficient/Lift Coefficient
P = W_body*V_∞*C_D/C_L

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 of Body*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 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 of Body (W_body), Freestream Velocity (V_∞), Drag Coefficient (C_D) & 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 -> 3013.636 = 221*30*0.5/1.1.

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_body*V_∞*C_D/C_L or Power = Weight of Body*Freestream Velocity*Drag Coefficient/Lift Coefficient. Weight of Body is the force acting on the object due to gravity, 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 & The Lift Coefficient 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 of Body*Freestream Velocity*Drag Coefficient/Lift Coefficient. To calculate Power required for given aerodynamic coefficients, you need Weight of Body (W_body), Freestream Velocity (V_∞), Drag Coefficient (C_D) & Lift Coefficient (C_L). With our tool, you need to enter the respective value for Weight of Body, Freestream Velocity, Drag Coefficient & 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 of Body, Freestream Velocity, Drag Coefficient & Lift Coefficient. We can use 2 other way(s) to calculate the same, which is/are as follows -

Power = Freestream Velocity*Thrust
Power = Drag Force*Freestream Velocity

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