Weight of aircraft for given required power Calculator

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Thrust and Power Requirements

Lift and Drag Requirements

✖Power is defined as the product of thrust force and velocity of aircraft.ⓘ Power [P]			+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%
✖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%

✖Weight of Body is the force acting on the object due to gravity.ⓘ Weight of aircraft for given required power [W_body]

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Formula

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Weight of aircraft for given required power

Formula

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

Example

`"220N"="3000W"*"1.1"/("30m/s"*"0.5")`

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Weight of aircraft for given required power Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

Variables Used

Weight of Body - (Measured in Newton) - Weight of Body is the force acting on the object due to gravity.
Power - (Measured in Watt) - Power is defined as the product of thrust force and velocity of aircraft.
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.
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.

STEP 1: Convert Input(s) to Base Unit

Power: 3000 Watt --> 3000 Watt No Conversion Required
Lift Coefficient: 1.1 --> No Conversion Required
Freestream Velocity: 30 Meter per Second --> 30 Meter per Second No Conversion Required
Drag Coefficient: 0.5 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

W_body = P*C_L/(V_∞*C_D) --> 3000*1.1/(30*0.5)

Evaluating ... ...

W_body = 220

STEP 3: Convert Result to Output's Unit

220 Newton --> No Conversion Required

FINAL ANSWER

220 Newton <-- Weight of Body

(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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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

Weight of aircraft for given required power Formula

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

What is aircraft gross weight?

The aircraft gross weight (also known as the all-up weight and abbreviated AUW) is the total aircraft weight at any moment during the flight or ground operation.

How to Calculate Weight of aircraft for given required power?

Weight of aircraft for given required power calculator uses Weight of Body = Power*Lift Coefficient/(Freestream Velocity*Drag Coefficient) to calculate the Weight of Body, The Weight of aircraft for given required power in a steady, level flight is a function of freestream velocity and aerodynamic coefficients. Weight of Body is denoted by W_body symbol.

How to calculate Weight of aircraft for given required power using this online calculator? To use this online calculator for Weight of aircraft for given required power, enter Power (P), Lift Coefficient (C_L), Freestream Velocity (V_∞) & Drag Coefficient (C_D) and hit the calculate button. Here is how the Weight of aircraft for given required power calculation can be explained with given input values -> 12.46667 = power__*1.1/(30*0.5).

FAQ

What is Weight of aircraft for given required power?

The Weight of aircraft for given required power in a steady, level flight is a function of freestream velocity and aerodynamic coefficients and is represented as W_body = P*C_L/(V_∞*C_D) or Weight of Body = Power*Lift Coefficient/(Freestream Velocity*Drag Coefficient). Power is defined as the product of thrust force and velocity of aircraft, 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, 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.

How to calculate Weight of aircraft for given required power?

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

In this formula, Weight of Body uses Power, Lift Coefficient, Freestream Velocity & Drag Coefficient. We can use 4 other way(s) to calculate the same, which is/are as follows -

Weight of Body = Lift Force+(Thrust*sin(Thrust angle))
Weight of Body = Dynamic Pressure*Area*Lift Coefficient
Weight of Body = Lift Coefficient*Thrust/Drag Coefficient
Weight of Body = Thrust*Lift-to-drag Ratio

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