Lift-to-Drag Ratio given required Thrust of Aircraft Calculator

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Lift and Drag Requirements

Thrust and Power Requirements

✖Weight of Body is the force acting on the object due to gravity.ⓘ Weight of Body [W_body]			+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%

✖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.ⓘ Lift-to-Drag Ratio given required Thrust of Aircraft [LD]

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Formula

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Lift-to-Drag Ratio given required Thrust of Aircraft

Formula

`"LD" = "W"_{"body"}/"T"`

Example

`"2.21"="221N"/"100N"`

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Lift-to-Drag Ratio given required Thrust of Aircraft Solution

STEP 0: Pre-Calculation Summary

Formula Used

Lift-to-Drag Ratio = Weight of Body/Thrust
LD = W_body/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 = W_body/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)

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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 Maiarutselvan V

PSG College of Technology (PSGCT), Coimbatore

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< 19 Lift and Drag Requirements Calculators

Lift Coefficient 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 at Minimum Thrust = (Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing)

Lift-Induced Drag Coefficient given required Thrust

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

Zero-Lift Drag Coefficient 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 given required Thrust of Aircraft

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

Freestream Velocity given Total Drag Force

Go Freestream Velocity = Power/Drag Force

Total Drag Force given required Power

Go Drag Force = Power/Freestream Velocity

Freestream Velocity 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 given required Thrust of Aircraft Formula

Lift-to-Drag Ratio = Weight of Body/Thrust
LD = W_body/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 given required Thrust of Aircraft?

Lift-to-Drag Ratio 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 given required Thrust of Aircraft is a measure used in aerodynamics to assess the efficiency of an aircraft's wing design, it is defined as the ratio of the lift generated by the wings to the drag produced by the aircraft as it moves through the air. Lift-to-Drag Ratio is denoted by LD symbol.

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

FAQ

What is Lift-to-Drag Ratio given required Thrust of Aircraft?

The Lift-to-Drag Ratio given required Thrust of Aircraft is a measure used in aerodynamics to assess the efficiency of an aircraft's wing design, it is defined as the ratio of the lift generated by the wings to the drag produced by the aircraft as it moves through the air and is represented as LD = W_body/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 given required Thrust of Aircraft?

The Lift-to-Drag Ratio given required Thrust of Aircraft is a measure used in aerodynamics to assess the efficiency of an aircraft's wing design, it is defined as the ratio of the lift generated by the wings to the drag produced by the aircraft as it moves through the air is calculated using Lift-to-Drag Ratio = Weight of Body/Thrust. To calculate Lift-to-Drag Ratio given required Thrust of Aircraft, you need Weight of Body (W_body) & 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.

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