Power required at sea-level condition Calculator

Category	Physics ↺
Physics	Flight Stability and Control ↺
Flight-Stability-And-Control	Airplane Performance ↺
Airplane-Performance	Altitude Effects on Power Required and Available ↺

✖Weight is a vector quantity and defined as the product of mass and acceleration acting on that massⓘ Weight [W]			+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 Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area.ⓘ Reference Area [S]			+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 required at sea-level is the power required by an aircraft to fly at the sea-level condition ⓘ Power required at sea-level condition [P_R,0]

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Vinay Mishra

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

Vinay Mishra has created this Calculator and 200+ more calculators!

Shikha Maurya

Indian Institute of Technology (IIT), Bombay

Shikha Maurya has verified this Calculator and 100+ 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

Power required at sea-level condition Formula

Power required at sea-level=sqrt(2*(Weight^3)*(Drag Coefficient^2)/([Std-Air-Density-Sea]*Reference Area*(lift coefficient^3)))
PR,0=sqrt(2*(W^3)*(CD^2)/([Std-Air-Density-Sea]*S*(CL^3)))

More formulas

Velocity at sea-level condition GO

Velocity at an altitude GO

Power required at an altitude GO

Velocity at an altitude for given velocity at sea-level condition GO

Power required at an altitude for given power required at sea-level condition GO

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Startups and large companies are developing electric planes, which are currently being tested. They could be in flight for commercial use in the next 20 years.

How to Calculate Power required at sea-level condition?

Power required at sea-level condition calculator uses Power required at sea-level=sqrt(2*(Weight^3)*(Drag Coefficient^2)/([Std-Air-Density-Sea]*Reference Area*(lift coefficient^3))) to calculate the Power required at sea-level, The Power required at sea-level condition for an aircraft is a function of the weight, reference area, and aerodynamic coefficients of the aircraft. Power required at sea-level and is denoted by P_R,0 symbol.

How to calculate Power required at sea-level condition using this online calculator? To use this online calculator for Power required at sea-level condition, enter Weight (W), Drag Coefficient (C_D), Reference Area (S) and lift coefficient (C_L) and hit the calculate button. Here is how the Power required at sea-level condition calculation can be explained with given input values -> 1804.073 = sqrt(2*(100^3)*(100^2)/([Std-Air-Density-Sea]*5*(10^3))).

FAQ

What is Power required at sea-level condition?

The Power required at sea-level condition for an aircraft is a function of the weight, reference area, and aerodynamic coefficients of the aircraft and is represented as P_R,0=sqrt(2*(W^3)*(C_D^2)/([Std-Air-Density-Sea]*S*(C_L^3))) or Power required at sea-level=sqrt(2*(Weight^3)*(Drag Coefficient^2)/([Std-Air-Density-Sea]*Reference Area*(lift coefficient^3))). Weight is a vector quantity and defined as the product of mass and acceleration acting on that mass, 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 Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area 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 at sea-level condition?

The Power required at sea-level condition for an aircraft is a function of the weight, reference area, and aerodynamic coefficients of the aircraft is calculated using Power required at sea-level=sqrt(2*(Weight^3)*(Drag Coefficient^2)/([Std-Air-Density-Sea]*Reference Area*(lift coefficient^3))). To calculate Power required at sea-level condition, you need Weight (W), Drag Coefficient (C_D), Reference Area (S) and lift coefficient (C_L). With our tool, you need to enter the respective value for Weight, Drag Coefficient, Reference Area and lift coefficient and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

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