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

STEP 0: Pre-Calculation Summary
Formula Used
Thrust = Weight of Body/Lift-to-drag Ratio
T = Wbody/LD
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.
Weight of Body - (Measured in Newton) - Weight of Body is the force acting on the object due to gravity.
Lift-to-drag Ratio - The Lift-to-drag ratio is the amount of lift generated by a wing or vehicle, divided by the aerodynamic drag it creates by moving through the air.
STEP 1: Convert Input(s) to Base Unit
Weight of Body: 221 Newton --> 221 Newton No Conversion Required
Lift-to-drag Ratio: 2.21 --> No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
T = Wbody/LD --> 221/2.21
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 Maiarutselvan V
PSG College of Technology (PSGCT), Coimbatore
Maiarutselvan V has verified this Calculator and 300+ 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 Lift-to-drag ratio Formula

Thrust = Weight of Body/Lift-to-drag Ratio
T = Wbody/LD

Should the Lift-to-drag ratio be high or low?

A greater or more favorable Lift-to-drag ratio is typically one of the major goals of aircraft design.

How to Calculate Thrust of aircraft required for given Lift-to-drag ratio?

Thrust of aircraft required for given Lift-to-drag ratio calculator uses Thrust = Weight of Body/Lift-to-drag Ratio to calculate the Thrust, The Thrust of aircraft required for given Lift-to-drag ratio for a steady, level flight is given by the weight of the aircraft divided by the Lift-to-drag ratio. Thrust is denoted by T symbol.

How to calculate Thrust of aircraft required for given Lift-to-drag ratio using this online calculator? To use this online calculator for Thrust of aircraft required for given Lift-to-drag ratio, enter Weight of Body (Wbody) & Lift-to-drag Ratio (LD) and hit the calculate button. Here is how the Thrust of aircraft required for given Lift-to-drag ratio calculation can be explained with given input values -> 1105 = 221/2.21.

FAQ

What is Thrust of aircraft required for given Lift-to-drag ratio?
The Thrust of aircraft required for given Lift-to-drag ratio for a steady, level flight is given by the weight of the aircraft divided by the Lift-to-drag ratio and is represented as T = Wbody/LD or Thrust = Weight of Body/Lift-to-drag Ratio. Weight of Body is the force acting on the object due to gravity & The Lift-to-drag ratio is the amount of lift generated by a wing or vehicle, divided by the aerodynamic drag it creates by moving through the air.
How to calculate Thrust of aircraft required for given Lift-to-drag ratio?
The Thrust of aircraft required for given Lift-to-drag ratio for a steady, level flight is given by the weight of the aircraft divided by the Lift-to-drag ratio is calculated using Thrust = Weight of Body/Lift-to-drag Ratio. To calculate Thrust of aircraft required for given Lift-to-drag ratio, you need Weight of Body (Wbody) & Lift-to-drag Ratio (LD). With our tool, you need to enter the respective value for Weight of Body & Lift-to-drag Ratio 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 Weight of Body & Lift-to-drag Ratio. 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 = 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))
  • Thrust = Power/Freestream Velocity
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