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

STEP 0: Pre-Calculation Summary
Formula Used
Lift-to-drag Ratio = Weight of Body/Thrust
LD = Wbody/T
This formula uses 3 Variables
Variables Used
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.
Weight of Body - (Measured in Newton) - Weight of Body is the force acting on the object due to gravity.
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
Weight of Body: 221 Newton --> 221 Newton No Conversion Required
Thrust: 100 Newton --> 100 Newton No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
LD = Wbody/T --> 221/100
Evaluating ... ...
LD = 2.21
STEP 3: Convert Result to Output's Unit
2.21 --> No Conversion Required
FINAL ANSWER
2.21 <-- Lift-to-drag Ratio
(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 Lift and Drag Requirements Calculators

Lift coefficient for given minimum required thrust
Go Lift Coefficient = sqrt(pi*Oswald Efficiency Factor*Aspect Ratio of a wing*((Thrust/(Dynamic Pressure*Area))-Zero Lift Drag Coefficient))
Zero-lift drag coefficient for given lift coefficient
Go Zero Lift Drag Coefficient = (Thrust/(Dynamic Pressure*Area))-((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing))
Zero-lift drag coefficient at minimum required thrust
Go Zero Lift Drag Coefficient = (Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing)
Lift-induced drag coefficient for given required thrust
Go Coefficient Of Drag Due to Lift = (Thrust/(Dynamic Pressure*Reference Area))-Zero Lift Drag Coefficient
Zero-lift drag coefficient for given required thrust
Go Zero Lift Drag Coefficient = (Thrust/(Dynamic Pressure*Reference Area))-Coefficient Of Drag Due to Lift
Lift for Unaccelerated Flight
Go Lift Force = Weight of Body-Thrust*sin(Thrust angle)
Coefficient of Drag for given thrust and weight
Go Drag Coefficient = Thrust*Lift Coefficient/Weight of Body
Coefficient of Lift for given thrust and weight
Go Lift Coefficient = Weight of Body*Drag Coefficient/Thrust
Drag for Level and Unaccelerated Flight at Negligible Thrust Angle
Go Drag Force = Dynamic Pressure*Area*Drag Coefficient
Lift for Level and Unaccelerated Flight at Negligible Thrust Angle
Go Lift Force = Dynamic Pressure*Area*Lift Coefficient
Drag for Level and Unaccelerated Flight
Go Drag Force = Thrust*(cos(Thrust angle))
Coefficient of Drag for given thrust-to-weight ratio
Go Drag Coefficient = Lift Coefficient*Thrust-to-Weight Ratio
Coefficient of Lift for given thrust-to-weight ratio
Go Lift Coefficient = Drag Coefficient/Thrust-to-Weight Ratio
Lift-to-drag ratio for given required thrust of aircraft
Go Lift-to-drag Ratio = Weight of Body/Thrust
Freestream Velocity for given total drag force
Go Freestream Velocity = Power/Drag Force
Total drag force for given required power
Go Drag Force = Power/Freestream Velocity
Freestream velocity for given required power
Go Freestream Velocity = Power/Thrust
Coefficient of Drag due to lift for minimum power required
Go Coefficient Of Drag Due to Lift = 3*Zero Lift Drag Coefficient
Zero-lift drag coefficient for minimum power required
Go Zero Lift Drag Coefficient = Coefficient Of Drag Due to Lift/3

Lift-to-drag ratio for given required thrust of aircraft Formula

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

How to determine the lift-to-drag ratio?

The Lift-to-drag ratio for an aircraft can be determined by flight test, by calculation, or by testing in a wind tunnel.

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

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

How to calculate Lift-to-drag ratio for given required thrust of aircraft using this online calculator? To use this online calculator for Lift-to-drag ratio for given required thrust of aircraft, enter Weight of Body (Wbody) & Thrust (T) and hit the calculate button. Here is how the Lift-to-drag ratio for given required thrust of aircraft calculation can be explained with given input values -> 2.21 = 221/100.

FAQ

What is Lift-to-drag ratio for given required thrust of aircraft?
The Lift-to-drag ratio for given required thrust of aircraft in a steady, level flight is given by the weight divided by the required thrust of an aircraft and is represented as LD = Wbody/T or Lift-to-drag Ratio = Weight of Body/Thrust. Weight of Body is the force acting on the object due to gravity & The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air.
How to calculate Lift-to-drag ratio for given required thrust of aircraft?
The Lift-to-drag ratio for given required thrust of aircraft in a steady, level flight is given by the weight divided by the required thrust of an aircraft is calculated using Lift-to-drag Ratio = Weight of Body/Thrust. To calculate Lift-to-drag ratio for given required thrust of aircraft, you need Weight of Body (Wbody) & Thrust (T). With our tool, you need to enter the respective value for Weight of Body & Thrust and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.
Let Others Know
Facebook
Twitter
Reddit
LinkedIn
Email
WhatsApp
Copied!