Weight of Aircraft for given Lift-to-Drag Ratio Calculator

✖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 [LD]			+10% -10%

✖Weight of Body is the force acting on the object due to gravity.ⓘ Weight of Aircraft for given Lift-to-Drag Ratio [W_body]

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Weight of Aircraft for given Lift-to-Drag Ratio Solution

STEP 0: Pre-Calculation Summary

Formula Used

Weight of Body = Thrust*Lift-to-Drag Ratio
W_body = T*LD
This formula uses 3 Variables

Variables Used

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.
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

Thrust: 100 Newton --> 100 Newton No Conversion Required
Lift-to-Drag Ratio: 2.21 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

W_body = T*LD --> 100*2.21

Evaluating ... ...

W_body = 221

STEP 3: Convert Result to Output's Unit

221 Newton --> No Conversion Required

FINAL ANSWER

221 Newton <-- Weight of Body

(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)

Weight of Aircraft for given Lift-to-Drag Ratio Formula

LaTeX Go

Weight of Body = Thrust*Lift-to-Drag Ratio
W_body = T*LD

Why is a high lift-to-drag ratio desirable for an aircraft?

Since a particular aircraft's required lift is set by its weight, delivering that lift with lower drag results directly in better fuel economy in aircraft, climb performance, and glide ratio.

How to Calculate Weight of Aircraft for given Lift-to-Drag Ratio?

Weight of Aircraft for given Lift-to-Drag Ratio calculator uses Weight of Body = Thrust*Lift-to-Drag Ratio to calculate the Weight of Body, The Weight of Aircraft for given Lift-to-Drag Ratio refers to the force exerted by gravity on the mass of the aircraft, it is the measure of the aircraft's heaviness or the amount of gravitational force pulling it downward, weight is what keeps an aircraft grounded until it generates sufficient lift to overcome it during takeoff, during flight, the aircraft's weight must be balanced by an equal and opposite force, typically provided by the aerodynamic lift generated by the wings. Weight of Body is denoted by W_body symbol.

How to calculate Weight of Aircraft for given Lift-to-Drag Ratio using this online calculator? To use this online calculator for Weight of Aircraft for given Lift-to-Drag Ratio, enter Thrust (T) & Lift-to-Drag Ratio (LD) and hit the calculate button. Here is how the Weight of Aircraft for given Lift-to-Drag Ratio calculation can be explained with given input values -> 20 = 100*2.21.

FAQ

What is Weight of Aircraft for given Lift-to-Drag Ratio?

The Weight of Aircraft for given Lift-to-Drag Ratio refers to the force exerted by gravity on the mass of the aircraft, it is the measure of the aircraft's heaviness or the amount of gravitational force pulling it downward, weight is what keeps an aircraft grounded until it generates sufficient lift to overcome it during takeoff, during flight, the aircraft's weight must be balanced by an equal and opposite force, typically provided by the aerodynamic lift generated by the wings and is represented as W_body = T*LD or Weight of Body = Thrust*Lift-to-Drag Ratio. The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air & 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 Weight of Aircraft for given Lift-to-Drag Ratio?

The Weight of Aircraft for given Lift-to-Drag Ratio refers to the force exerted by gravity on the mass of the aircraft, it is the measure of the aircraft's heaviness or the amount of gravitational force pulling it downward, weight is what keeps an aircraft grounded until it generates sufficient lift to overcome it during takeoff, during flight, the aircraft's weight must be balanced by an equal and opposite force, typically provided by the aerodynamic lift generated by the wings is calculated using Weight of Body = Thrust*Lift-to-Drag Ratio. To calculate Weight of Aircraft for given Lift-to-Drag Ratio, you need Thrust (T) & Lift-to-Drag Ratio (LD). With our tool, you need to enter the respective value for Thrust & 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 Weight of Body?

In this formula, Weight of Body uses Thrust & Lift-to-Drag Ratio. We can use 3 other way(s) to calculate the same, which is/are as follows -

Weight of Body = Lift Force+(Thrust*sin(Thrust Angle))
Weight of Body = Dynamic Pressure*Area*Lift Coefficient
Weight of Body = Lift Coefficient*Thrust/Drag Coefficient

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