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

✖Weight of Body is the force acting on the object due to gravity.ⓘ Weight of Body [W_body]			+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 [LD]			+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 Lift-to-drag ratio [T]

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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 = W_body/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 = W_body/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)

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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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< Thrust and Power Requirements Calculators

Thrust Angle for Unaccelerated Level Flight for given Lift

LaTeX Go Thrust Angle = asin((Weight of Body-Lift Force)/Thrust)

Weight of Aircraft in Level, Unaccelerated Flight

LaTeX Go Weight of Body = Lift Force+(Thrust*sin(Thrust Angle))

Thrust for Level and Unaccelerated Flight

LaTeX Go Thrust = Drag Force/(cos(Thrust Angle))

Thrust Angle for Unaccelerated Level Flight for given Drag

LaTeX Go Thrust Angle = acos(Drag Force/Thrust)

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

LaTeX Go

Thrust = Weight of Body/Lift-to-Drag Ratio
T = W_body/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 is the amount of propulsive force needed to maintain level flight while achieving the specified ratio of lift to drag, this concept is fundamental in aerospace engineering, as it helps determine the performance characteristics and efficiency of an aircraft. 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 (W_body) & 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 is the amount of propulsive force needed to maintain level flight while achieving the specified ratio of lift to drag, this concept is fundamental in aerospace engineering, as it helps determine the performance characteristics and efficiency of an aircraft and is represented as T = W_body/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 is the amount of propulsive force needed to maintain level flight while achieving the specified ratio of lift to drag, this concept is fundamental in aerospace engineering, as it helps determine the performance characteristics and efficiency of an aircraft 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 (W_body) & 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 3 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

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