Weight of aircraft for given excess power Calculator

Category	Physics ↺
Physics	Flight Stability and Control ↺
Flight-Stability-And-Control	Airplane Performance ↺
Airplane-Performance	Rate of Climb ↺

✖Excess Power is defined as the difference between the power available and the power required at a particular speed and altitude of aircraftⓘ Excess Power [P_excess]			+10% -10%
✖The Rate of Climb (RoC) is defined as the aircraft's vertical speed – the positive or negative rate of altitude change with respect to time.ⓘ Rate of Climb [R/C]			+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 excess power [W]

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Weight of aircraft for given excess power

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!

< 7 Other formulas that you can solve using the same Inputs

Velocity of aircraft for given excess power

Velocity=Excess Power/(Thrust of an aircraft-Drag Force) GO

Thrust available for given excess power

Thrust force=Drag Force+(Excess Power/Velocity) GO

Total Drag for given excess power

Drag Force=Thrust force-(Excess Power/Velocity) GO

Flight path angle at a given rate of climb

Flight path angle=asin(Rate of Climb/Velocity) GO

Velocity of aircraft at a given rate of climb

Velocity=Rate of Climb/sin(Flight path angle) GO

Rate of Climb for given excess power

Rate of Climb=Excess Power/Weight GO

Excess power for given rate of climb

Excess Power=Rate of Climb*Weight GO

< 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 required power

Weight=Power*lift coefficient/(Freestream Velocity*Drag Coefficient) 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 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 excess power Formula

Weight=Excess Power/Rate of Climb
W=P<sub>excess</sub>/R/C

More formulas

Rate of Climb GO

Velocity of aircraft at a given rate of climb GO

Flight path angle at a given rate of climb GO

Excess power GO

Thrust available for given excess power GO

Total Drag for given excess power GO

Velocity of aircraft for given excess power GO

Rate of Climb for given excess power GO

Excess power for given rate of climb GO

What angle do planes take off?

Planes slowly angle up during take off at about 2-3 degrees per second for a Boeing 747. The average passenger plane has a maximum take-off angle of about 10-15 degrees.

How to Calculate Weight of aircraft for given excess power?

Weight of aircraft for given excess power calculator uses Weight=Excess Power/Rate of Climb to calculate the Weight, The Weight of aircraft for given excess power of an aircraft is given by the ratio of excess power and rate of climb of the aircraft. Weight and is denoted by W symbol.

How to calculate Weight of aircraft for given excess power using this online calculator? To use this online calculator for Weight of aircraft for given excess power, enter Excess Power (P_excess) and Rate of Climb (R/C) and hit the calculate button. Here is how the Weight of aircraft for given excess power calculation can be explained with given input values -> 300 = 1500/5.

FAQ

What is Weight of aircraft for given excess power?

The Weight of aircraft for given excess power of an aircraft is given by the ratio of excess power and rate of climb of the aircraft and is represented as W=P_excess/R/C or Weight=Excess Power/Rate of Climb. Excess Power is defined as the difference between the power available and the power required at a particular speed and altitude of aircraft and The Rate of Climb (RoC) is defined as the aircraft's vertical speed – the positive or negative rate of altitude change with respect to time.

How to calculate Weight of aircraft for given excess power?

The Weight of aircraft for given excess power of an aircraft is given by the ratio of excess power and rate of climb of the aircraft is calculated using Weight=Excess Power/Rate of Climb. To calculate Weight of aircraft for given excess power, you need Excess Power (P_excess) and Rate of Climb (R/C). With our tool, you need to enter the respective value for Excess Power and Rate of Climb 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 Excess Power and Rate of Climb. 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=Power*lift coefficient/(Freestream Velocity*Drag Coefficient)
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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