Power required for given required thrust of aircraft Calculator

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Thrust and Power Requirements

Lift and Drag Requirements

✖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%
✖The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air.ⓘ Thrust [T]			+10% -10%

✖Power is defined as the product of thrust force and velocity of aircraft.ⓘ Power required for given required thrust of aircraft [P]

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Formula

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Power required for given required thrust of aircraft

Formula

`"P" = "V"_{"∞"}*"T"`

Example

`"3000W"="30m/s"*"100N"`

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Power required for given required thrust of aircraft Solution

STEP 0: Pre-Calculation Summary

Formula Used

Power = Freestream Velocity*Thrust
P = V_∞*T
This formula uses 3 Variables

Variables Used

Power - (Measured in Watt) - Power is defined as the product of thrust force and velocity of aircraft.
Freestream Velocity - (Measured in Meter per Second) - 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.
Thrust - (Measured in Newton) - The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air.

STEP 1: Convert Input(s) to Base Unit

Freestream Velocity: 30 Meter per Second --> 30 Meter per Second No Conversion Required
Thrust: 100 Newton --> 100 Newton No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

P = V_∞*T --> 30*100

Evaluating ... ...

P = 3000

STEP 3: Convert Result to Output's Unit

3000 Watt --> No Conversion Required

FINAL ANSWER

3000 Watt <-- Power

(Calculation completed in 00.004 seconds)

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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 Chilvera Bhanu Teja

Institute of Aeronautical Engineering (IARE), Hyderabad

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< 19 Thrust and Power Requirements Calculators

Minimum Thrust required for given weight

Go Thrust = (Dynamic Pressure*Area*Zero Lift Drag Coefficient)+((Weight of Body^2)/(Dynamic Pressure*Area*pi*Oswald Efficiency Factor*Aspect Ratio of a wing))

Minimum Thrust required for given lift coefficient

Go Thrust = Dynamic Pressure*Area*(Zero Lift Drag Coefficient+((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing)))

Minimum Thrust of aircraft required

Go Thrust = Dynamic Pressure*Reference Area*(Zero Lift Drag Coefficient+Coefficient Of Drag Due to Lift)

Weight of aircraft for given required power

Go Weight of Body = Power*Lift Coefficient/(Freestream Velocity*Drag Coefficient)

Power required for given aerodynamic coefficients

Go Power = Weight of Body*Freestream Velocity*Drag Coefficient/Lift Coefficient

Thrust Angle for Unaccelerated Level Flight for given Lift

Go Thrust angle = asin((Weight of Body-Lift Force)/Thrust)

Weight of aircraft in level, unaccelerated flight

Go Weight of Body = Lift Force+(Thrust*sin(Thrust angle))

Weight of aircraft for given coefficients of lift and drag

Go Weight of Body = Lift Coefficient*Thrust/Drag Coefficient

Thrust for given coefficients of lift and drag

Go Thrust = Drag Coefficient*Weight of Body/Lift Coefficient

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

Go Weight of Body = Dynamic Pressure*Area*Lift Coefficient

Thrust of aircraft required for level, unaccelerated flight

Go Thrust = Dynamic Pressure*Area*Drag Coefficient

Thrust for Level and Unaccelerated Flight

Go Thrust = Drag Force/(cos(Thrust angle))

Thrust Angle for Unaccelerated Level Flight for given Drag

Go Thrust angle = acos(Drag Force/Thrust)

Thrust-to-weight ratio

Go Thrust-to-Weight Ratio = Drag Coefficient/Lift Coefficient

Thrust of aircraft required for given Lift-to-drag ratio

Go Thrust = Weight of Body/Lift-to-drag Ratio

Weight of aircraft for given Lift-to-drag ratio

Go Weight of Body = Thrust*Lift-to-drag Ratio

Power required for given total drag force

Go Power = Drag Force*Freestream Velocity

Power required for given required thrust of aircraft

Go Power = Freestream Velocity*Thrust

Thrust of aircraft required for given required power

Go Thrust = Power/Freestream Velocity

Power required for given required thrust of aircraft Formula

Power = Freestream Velocity*Thrust
P = V_∞*T

What is the powerplant of an airplane?

In simple terms, an aircraft power plant is an engine. It is made up of many components, such as cylinders, pistons, and fans, which help produce the energy needed to propel an aircraft.

How to Calculate Power required for given required thrust of aircraft?

Power required for given required thrust of aircraft calculator uses Power = Freestream Velocity*Thrust to calculate the Power, The Power required for given required thrust of aircraft for a steady, level flight is the product of freestream velocity and thrust required for an aircraft. Power is denoted by P symbol.

How to calculate Power required for given required thrust of aircraft using this online calculator? To use this online calculator for Power required for given required thrust of aircraft, enter Freestream Velocity (V_∞) & Thrust (T) and hit the calculate button. Here is how the Power required for given required thrust of aircraft calculation can be explained with given input values -> 3000 = 30*100.

FAQ

What is Power required for given required thrust of aircraft?

The Power required for given required thrust of aircraft for a steady, level flight is the product of freestream velocity and thrust required for an aircraft and is represented as P = V_∞*T or Power = Freestream Velocity*Thrust. 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 & The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air.

How to calculate Power required for given required thrust of aircraft?

The Power required for given required thrust of aircraft for a steady, level flight is the product of freestream velocity and thrust required for an aircraft is calculated using Power = Freestream Velocity*Thrust. To calculate Power required for given required thrust of aircraft, you need Freestream Velocity (V_∞) & Thrust (T). With our tool, you need to enter the respective value for Freestream Velocity & Thrust 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?

In this formula, Power uses Freestream Velocity & Thrust. We can use 2 other way(s) to calculate the same, which is/are as follows -

Power = Weight of Body*Freestream Velocity*Drag Coefficient/Lift Coefficient
Power = Drag Force*Freestream Velocity

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