Weight of aircraft for given required power Calculator

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

✖Power is the amount of energy liberated per second in a device.ⓘ Power [P]			+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%
✖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 is a vector quantity and defined as the product of mass and acceleration acting on that massⓘ Weight of aircraft for given required power [W]

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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!

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< 9 Other formulas that calculate the same Output

Weight of aircraft during ground roll

Weight=(Rolling Resistance/Coefficient of Rolling Friction)+Lift force GO

Weight of aircraft for given coefficients of lift and drag

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

Weight of aircraft in level, unaccelerated flight

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

Weight of aircraft for given Lift-to-drag ratio

Weight=Thrust of an aircraft*Lift-to-drag ratio GO

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

Weight=Dynamic Pressure*Area*lift coefficient GO

Total weight of the ram of hydraulic accumulator

Weight=Pressure intensity*Area of sliding ram GO

Weight of aircraft for given excess power

Weight=Excess Power/Rate of Climb GO

Weight during level turn

Weight=Lift force*cos(Bank angle) GO

Weight for a given load factor

Weight=Lift force/Load factor GO

Weight of aircraft for given required power Formula

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

More formulas

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Thrust required for given required power GO

Freestream velocity for given required power GO

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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 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=Power*lift coefficient/(Freestream Velocity*Drag Coefficient) to calculate the Weight, The Weight of aircraft for given required power in a steady, level flight is a function of freestream velocity and aerodynamic coefficients. Weight and is denoted by W 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_∞) and 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 -> 0.1 = 100*10/(100*100).

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=P*C_L/(V_∞*C_D) or Weight=Power*lift coefficient/(Freestream Velocity*Drag Coefficient). Power is the amount of energy liberated per second in a device, 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. , 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 and 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=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_∞) and Drag Coefficient (C_D). With our tool, you need to enter the respective value for Power, lift coefficient, Freestream Velocity and 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?

In this formula, Weight uses Power, lift coefficient, Freestream Velocity and Drag Coefficient. We can use 9 other way(s) to calculate the same, which is/are as follows -

Weight=Lift force+(Thrust of an aircraft*sin(Thrust angle))
Weight=Dynamic Pressure*Area*lift coefficient
Weight=lift coefficient*Thrust of an aircraft/Drag Coefficient
Weight=Thrust of an aircraft*Lift-to-drag ratio
Weight=Excess Power/Rate of Climb
Weight=(Rolling Resistance/Coefficient of Rolling Friction)+Lift force
Weight=Lift force*cos(Bank angle)
Weight=Lift force/Load factor
Weight=Pressure intensity*Area of sliding ram

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