Thrust of aircraft required for given required power Calculator

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Thrust and Power Requirements

Lift and Drag Requirements

✖Power is defined as the product of thrust force and velocity of aircraft.ⓘ Power [P]			+10% -10%
✖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 of aircraft required for given required power [T]

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Formula

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Thrust of aircraft required for given required power

Formula

`"T" = "P"/"V"_{"∞"}`

Example

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

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Thrust of aircraft required for given required power Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

Variables Used

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.
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.

STEP 1: Convert Input(s) to Base Unit

Power: 3000 Watt --> 3000 Watt No Conversion Required
Freestream Velocity: 30 Meter per Second --> 30 Meter per Second No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

T = P/V_∞ --> 3000/30

Evaluating ... ...

T = 100

STEP 3: Convert Result to Output's Unit

100 Newton --> No Conversion Required

FINAL ANSWER

100 Newton <-- Thrust

(Calculation completed in 00.020 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 Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

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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

Thrust of aircraft required for given required power Formula

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

What is the approximate power required for a commercial aircraft?

The power required to keep a Boeing 737-300 flying at a constant altitude and speed is 7200000 watts.

How to Calculate Thrust of aircraft required for given required power?

Thrust of aircraft required for given required power calculator uses Thrust = Power/Freestream Velocity to calculate the Thrust, The Thrust of aircraft required for given required power refers to the force generated by its engines or propulsion system to overcome aerodynamic drag and propel the aircraft forward through the air, it is the force exerted in the direction opposite to the aircraft's motion relative to the air. Thrust is essential for achieving and maintaining flight, enabling an aircraft to ascend, descend, maintain level flight, and control its speed and direction. Thrust is denoted by T symbol.

How to calculate Thrust of aircraft required for given required power using this online calculator? To use this online calculator for Thrust of aircraft required for given required power, enter Power (P) & Freestream Velocity (V_∞) and hit the calculate button. Here is how the Thrust of aircraft required for given required power calculation can be explained with given input values -> 5.666667 = power__/30.

FAQ

What is Thrust of aircraft required for given required power?

The Thrust of aircraft required for given required power refers to the force generated by its engines or propulsion system to overcome aerodynamic drag and propel the aircraft forward through the air, it is the force exerted in the direction opposite to the aircraft's motion relative to the air. Thrust is essential for achieving and maintaining flight, enabling an aircraft to ascend, descend, maintain level flight, and control its speed and direction and is represented as T = P/V_∞ or Thrust = Power/Freestream Velocity. Power is defined as the product of thrust force and velocity of aircraft & 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.

How to calculate Thrust of aircraft required for given required power?

The Thrust of aircraft required for given required power refers to the force generated by its engines or propulsion system to overcome aerodynamic drag and propel the aircraft forward through the air, it is the force exerted in the direction opposite to the aircraft's motion relative to the air. Thrust is essential for achieving and maintaining flight, enabling an aircraft to ascend, descend, maintain level flight, and control its speed and direction is calculated using Thrust = Power/Freestream Velocity. To calculate Thrust of aircraft required for given required power, you need Power (P) & Freestream Velocity (V_∞). With our tool, you need to enter the respective value for Power & Freestream Velocity 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 Thrust?

In this formula, Thrust uses Power & Freestream Velocity. We can use 7 other way(s) to calculate the same, which is/are as follows -

Thrust = Drag Force/(cos(Thrust angle))
Thrust = Dynamic Pressure*Area*Drag Coefficient
Thrust = Drag Coefficient*Weight of Body/Lift Coefficient
Thrust = Weight of Body/Lift-to-drag Ratio
Thrust = Dynamic Pressure*Reference Area*(Zero Lift Drag Coefficient+Coefficient Of Drag Due to Lift)
Thrust = Dynamic Pressure*Area*(Zero Lift Drag Coefficient+((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing)))
Thrust = (Dynamic Pressure*Area*Zero Lift Drag Coefficient)+((Weight of Body^2)/(Dynamic Pressure*Area*pi*Oswald Efficiency Factor*Aspect Ratio of a wing))

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