Power required at Altitude Calculator

✖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 Density of a material shows the denseness of that material in a specific given area. This is taken as mass per unit volume of a given object.ⓘ Density [ρ₀]			+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 Altitude is the power required for an aircraft to fly with a specific velocity at an altitude for a given altitude (or density).ⓘ Power required at Altitude [P_R,alt]

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Power required at Altitude Solution

STEP 0: Pre-Calculation Summary

Formula Used

Power Required at Altitude = sqrt((2*Weight of Body^3*Drag Coefficient^2)/(Density*Reference Area*Lift Coefficient^3))
P_R,alt = sqrt((2*W_body^3*C_D^2)/(ρ₀*S*C_L^3))
This formula uses 1 Functions, 6 Variables

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 Altitude - (Measured in Watt) - Power Required at Altitude is the power required for an aircraft to fly with a specific velocity at an altitude for a given altitude (or density).
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.
Density - (Measured in Kilogram per Cubic Meter) - The Density of a material shows the denseness of that material in a specific given area. This is taken as mass per unit volume of a given object.
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
Density: 997 Kilogram per Cubic Meter --> 997 Kilogram per Cubic Meter 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,alt = sqrt((2*W_body^3*C_D^2)/(ρ₀*S*C_L^3)) --> sqrt((2*750^3*1.134^2)/(997*91.05*0.29^3))

Evaluating ... ...

P_R,alt = 700.060213980307

STEP 3: Convert Result to Output's Unit

700.060213980307 Watt --> No Conversion Required

FINAL ANSWER

700.060213980307 ≈ 700.0602 Watt <-- Power Required at Altitude

(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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< Preliminary Aerodynamics Calculators

Power required at sea-level conditions

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

Power required at Altitude

LaTeX Go Power Required at Altitude = sqrt((2*Weight of Body^3*Drag Coefficient^2)/(Density*Reference Area*Lift Coefficient^3))

Velocity at Sea-Level given Lift Coefficient

LaTeX Go Velocity at Sea-Level = sqrt((2*Weight of Body)/([Std-Air-Density-Sea]*Reference Area*Lift Coefficient))

Velocity at Altitude

LaTeX Go Velocity at an Altitude = sqrt(2*Weight of Body/(Density*Reference Area*Lift Coefficient))

Power required at Altitude Formula

LaTeX Go

Power Required at Altitude = sqrt((2*Weight of Body^3*Drag Coefficient^2)/(Density*Reference Area*Lift Coefficient^3))
P_R,alt = sqrt((2*W_body^3*C_D^2)/(ρ₀*S*C_L^3))

How fast can you go in a commercial airliner?

For civil aircraft, there is an airspeed limit of Mach 1 which is 667 knots or around 767 miles per hour.

How to Calculate Power required at Altitude?

Power required at Altitude calculator uses Power Required at Altitude = sqrt((2*Weight of Body^3*Drag Coefficient^2)/(Density*Reference Area*Lift Coefficient^3)) to calculate the Power Required at Altitude, Power required at Altitude is a measure of the minimum power needed by an aircraft to overcome the drag forces and maintain a steady altitude, influenced by factors such as body weight, drag coefficient, air density, and lift coefficient. Power Required at Altitude is denoted by P_R,alt symbol.

How to calculate Power required at Altitude using this online calculator? To use this online calculator for Power required at Altitude, enter Weight of Body (W_body), Drag Coefficient (C_D), Density (ρ₀), Reference Area (S) & Lift Coefficient (C_L) and hit the calculate button. Here is how the Power required at Altitude calculation can be explained with given input values -> 699.8681 = sqrt((2*750^3*1.134^2)/(997*91.05*0.29^3)).

FAQ

What is Power required at Altitude?

Power required at Altitude is a measure of the minimum power needed by an aircraft to overcome the drag forces and maintain a steady altitude, influenced by factors such as body weight, drag coefficient, air density, and lift coefficient and is represented as P_R,alt = sqrt((2*W_body^3*C_D^2)/(ρ₀*S*C_L^3)) or Power Required at Altitude = sqrt((2*Weight of Body^3*Drag Coefficient^2)/(Density*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 Density of a material shows the denseness of that material in a specific given area. This is taken as mass per unit volume of a given object, 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 Altitude?

Power required at Altitude is a measure of the minimum power needed by an aircraft to overcome the drag forces and maintain a steady altitude, influenced by factors such as body weight, drag coefficient, air density, and lift coefficient is calculated using Power Required at Altitude = sqrt((2*Weight of Body^3*Drag Coefficient^2)/(Density*Reference Area*Lift Coefficient^3)). To calculate Power required at Altitude, you need Weight of Body (W_body), Drag Coefficient (C_D), Density (ρ₀), Reference Area (S) & Lift Coefficient (C_L). With our tool, you need to enter the respective value for Weight of Body, Drag Coefficient, Density, 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.

How many ways are there to calculate Power Required at Altitude?

In this formula, Power Required at Altitude uses Weight of Body, Drag Coefficient, Density, Reference Area & Lift Coefficient. We can use 1 other way(s) to calculate the same, which is/are as follows -

Power Required at Altitude = Power Required at Sea-level*sqrt([Std-Air-Density-Sea]/Density)

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