Weight of aircraft for given Lift-to-drag ratio Calculator

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Thrust and Power Requirements

Lift and Drag Requirements

✖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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Formula

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Weight of aircraft for given Lift-to-drag ratio

Formula

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

Example

`"221N"="100N"*"2.21"`

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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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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

Weight of aircraft for given Lift-to-drag ratio Formula

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 in a steady, level flight is given by the product of required thrust and the lift-to-drag ratio of aircraft. 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 in a steady, level flight is given by the product of required thrust and the lift-to-drag ratio of aircraft 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 in a steady, level flight is given by the product of required thrust and the lift-to-drag ratio of aircraft 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 4 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
Weight of Body = Power*Lift Coefficient/(Freestream Velocity*Drag Coefficient)

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