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 00.004 seconds)

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 Sanjay Krishna
Amrita School of Engineering (ASE), Vallikavu
Sanjay Krishna has verified this Calculator and 200+ more calculators!

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 for a steady, level flight is given by the required power divided by the freestream velocity of the aircraft. 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 for a steady, level flight is given by the required power divided by the freestream velocity of the aircraft 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 for a steady, level flight is given by the required power divided by the freestream velocity of the aircraft 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))
Let Others Know
Facebook
Twitter
Reddit
LinkedIn
Email
WhatsApp
Copied!