Power required at sea-level conditions Calculator

⤿

Introduction and Governing Equations

Aircraft Design

Aircraft Performance

Static Stability and Control

⤿

Preliminary Aerodynamics

Aircraft Dynamics Nomenclature

Atmosphere and Gas Properties

Lift and Drag Polar

✖Weight of body is the force acting on the object due to gravity.ⓘ Weight of body [W_body]			+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 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 conditions [P_R,0]

⎘ Copy

👎

Formula

✖

Power required at sea-level conditions

Formula

`"P"_{"R,0"} = sqrt((2*"W"_{"body"}^3*"C"_{"D"}^2)/("[Std-Air-Density-Sea]"*"S"*"C"_{"L"}^3))`

Example

`"19939.17W"=sqrt((2*("750N")^3*("1.134")^2)/("[Std-Air-Density-Sea]"*"91.05m²"*("0.29")^3))`

Calculator

LaTeX

Reset

👍

Download Physics Formula PDF PDF Image

Power required at sea-level conditions Solution

STEP 0: Pre-Calculation Summary

Formula Used

Power required at sea-level = sqrt((2*Weight of body^3*Drag Coefficient^2)/([Std-Air-Density-Sea]*Reference Area*Lift Coefficient^3))
P_R,0 = sqrt((2*W_body^3*C_D^2)/([Std-Air-Density-Sea]*S*C_L^3))
This formula uses 1 Constants, 1 Functions, 5 Variables

Constants Used

[Std-Air-Density-Sea] - Standard air density at sea-level conditions Value Taken As 1.229

Functions Used

sqrt - A square root function is a function that takes a non-negative number as an input and returns the square root of the given input number., sqrt(Number)

Variables Used

Power required at sea-level - (Measured in Watt) - Power required at sea-level is the power required by an aircraft to fly at the sea-level condition.
Weight of body - (Measured in Newton) - Weight of body is the force acting on the object due to gravity.
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.
Reference Area - (Measured in Square Meter) - 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.
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: 750 Newton --> 750 Newton No Conversion Required
Drag Coefficient: 1.134 --> No Conversion Required
Reference Area: 91.05 Square Meter --> 91.05 Square Meter No Conversion Required
Lift Coefficient: 0.29 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

P_R,0 = sqrt((2*W_body^3*C_D^2)/([Std-Air-Density-Sea]*S*C_L^3)) --> sqrt((2*750^3*1.134^2)/([Std-Air-Density-Sea]*91.05*0.29^3))

Evaluating ... ...

P_R,0 = 19939.168070484

STEP 3: Convert Result to Output's Unit

19939.168070484 Watt --> No Conversion Required

FINAL ANSWER

19939.168070484 ≈ 19939.17 Watt <-- Power required at sea-level

(Calculation completed in 00.004 seconds)

You are here -

Home » Physics » Aircraft Mechanics » Introduction and Governing Equations » Preliminary Aerodynamics » Power required at sea-level conditions

Credits

Created by Vinay Mishra

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

Vinay Mishra has created this Calculator and 300+ more calculators!

Verified by Shikha Maurya

Indian Institute of Technology (IIT), Bombay

Shikha Maurya has verified this Calculator and 200+ more calculators!

< 17 Preliminary Aerodynamics Calculators

Power required at sea-level conditions

Go Power required at sea-level = sqrt((2*Weight of body^3*Drag Coefficient^2)/([Std-Air-Density-Sea]*Reference Area*Lift Coefficient^3))

Mach Number-2

Go Mach number 2 = sqrt(((((Heat Capacity Ratio-1)*Mach Number^(2)+2))/(2*Heat Capacity Ratio*Mach Number^(2)-(Heat Capacity Ratio-1))))

Power required at Altitude

Go Power required at an altitude = sqrt((2*Weight of body^3*Drag Coefficient^2)/(Density*Reference Area*Lift Coefficient^3))

Velocity at Sea-level given Lift Coefficient

Go Velocity at sea-level = sqrt((2*Weight of body)/([Std-Air-Density-Sea]*Reference Area*Lift Coefficient))

Dynamic pressure given gas constant

Go Dynamic Pressure = 1/2*Ambient air density*Mach Number^2*Specific Heat of Air*Gas Constant*Temperature

Velocity at Altitude

Go Velocity at an altitude = sqrt(2*Weight of body/(Density*Reference Area*Lift Coefficient))

Power required at Altitude given Power at sea-level

Go Power required at an altitude = Power required at sea-level*sqrt([Std-Air-Density-Sea]/Density)

Velocity at Altitude given Velocity at Sea-Level

Go Velocity at an altitude = Velocity at sea-level*sqrt([Std-Air-Density-Sea]/Density)

Dynamic pressure given induced drag

Go Dynamic Pressure = Lift Force^2/(pi*Induced Drag*Lateral plane span^2)

Dynamic pressure given mach number

Go Dynamic Pressure = 1/2*Ambient air density*(Mach Number*Sonic speed)^2

Dynamic pressure given normal pressure

Go Dynamic Pressure = 1/2*Specific Heat of Air*Pressure*Mach Number^2

Flight speed given dynamic pressure

Go Flight speed = sqrt((2*Dynamic Pressure)/Ambient air density)

Dynamic pressure aircraft

Go Dynamic Pressure = 1/2*Ambient air density*Flight speed^2

Dynamic pressure given lift coefficient

Go Dynamic Pressure = Lift Force/Lift Coefficient

Dynamic pressure given drag coefficient

Go Dynamic Pressure = Drag Force/Drag Coefficient

Aerodynamic force

Go Aerodynamic Force = Drag Force+Lift Force

Mach number of moving object

Go Mach Number = Velocity/Speed of Sound

Power required at sea-level conditions Formula

Power required at sea-level = sqrt((2*Weight of body^3*Drag Coefficient^2)/([Std-Air-Density-Sea]*Reference Area*Lift Coefficient^3))
P_R,0 = sqrt((2*W_body^3*C_D^2)/([Std-Air-Density-Sea]*S*C_L^3))

Will planes ever be electric?

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 conditions?

Power required at sea-level conditions calculator uses Power required at sea-level = sqrt((2*Weight of body^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 conditions for an aircraft is a function of the weight, reference area, and aerodynamic coefficients of the aircraft. Power required at sea-level is denoted by P_R,0 symbol.

How to calculate Power required at sea-level conditions using this online calculator? To use this online calculator for Power required at sea-level conditions, enter Weight of body (W_body), Drag Coefficient (C_D), Reference Area (S) & Lift Coefficient (C_L) and hit the calculate button. Here is how the Power required at sea-level conditions calculation can be explained with given input values -> 19933.7 = sqrt((2*750^3*1.134^2)/([Std-Air-Density-Sea]*91.05*0.29^3)).

FAQ

What is Power required at sea-level conditions?

The Power required at sea-level conditions 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_body^3*C_D^2)/([Std-Air-Density-Sea]*S*C_L^3)) or Power required at sea-level = sqrt((2*Weight of body^3*Drag Coefficient^2)/([Std-Air-Density-Sea]*Reference Area*Lift Coefficient^3)). Weight of body is the force acting on the object due to gravity, 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 & 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 at sea-level conditions?

The Power required at sea-level conditions 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 of body^3*Drag Coefficient^2)/([Std-Air-Density-Sea]*Reference Area*Lift Coefficient^3)). To calculate Power required at sea-level conditions, you need Weight of body (W_body), Drag Coefficient (C_D), Reference Area (S) & Lift Coefficient (C_L). With our tool, you need to enter the respective value for Weight of body, Drag Coefficient, Reference Area & Lift Coefficient and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

Home

FREE PDFs

🔍 Search