Weight of Aircraft for given Coefficients of Lift and Drag Calculator

✖The Lift Coefficient is a dimensionless coefficient that relates the lift generated by a lifting body to the fluid density around the body, the fluid velocity and an associated reference area.ⓘ Lift Coefficient [C_L]			+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%
✖Drag Coefficient is a dimensionless quantity that is used to quantify the drag or resistance of an object in a fluid environment, such as air or water.ⓘ Drag Coefficient [C_D]			+10% -10%

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

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Formula

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Weight of Aircraft for given Coefficients of Lift and Drag

Formula

W body = C L \cdot \frac{T}{C D}

Example

220 N = 1.1 \cdot \frac{100 N}{0.5}

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Weight of Aircraft for given Coefficients of Lift and Drag Solution

STEP 0: Pre-Calculation Summary

Formula Used

Weight of Body = Lift Coefficient*Thrust/Drag Coefficient
W_body = C_L*T/C_D
This formula uses 4 Variables

Variables Used

Weight of Body - (Measured in Newton) - Weight of Body is the force acting on the object due to gravity.
Lift Coefficient - The Lift Coefficient is a dimensionless coefficient that relates the lift generated by a lifting body to the fluid density around the body, the fluid velocity and an associated reference area.
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.
Drag Coefficient - Drag Coefficient is a dimensionless quantity that is used to quantify the drag or resistance of an object in a fluid environment, such as air or water.

STEP 1: Convert Input(s) to Base Unit

Lift Coefficient: 1.1 --> No Conversion Required
Thrust: 100 Newton --> 100 Newton No Conversion Required
Drag Coefficient: 0.5 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

W_body = C_L*T/C_D --> 1.1*100/0.5

Evaluating ... ...

W_body = 220

STEP 3: Convert Result to Output's Unit

220 Newton --> No Conversion Required

FINAL ANSWER

220 Newton <-- Weight of Body

(Calculation completed in 00.020 seconds)

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Created by Vinay Mishra

Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune

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PSG College of Technology (PSGCT), Coimbatore

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< Thrust and Power Requirements Calculators

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))

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)

Weight of Aircraft for given Coefficients of Lift and Drag Formula

Weight of Body = Lift Coefficient*Thrust/Drag Coefficient
W_body = C_L*T/C_D

What is a good indicator of the maneuverability of a combat aircraft?

The thrust-to-weight ratio of a combat aircraft is a good indicator of the maneuverability of the aircraft.

How to Calculate Weight of Aircraft for given Coefficients of Lift and Drag?

Weight of Aircraft for given Coefficients of Lift and Drag calculator uses Weight of Body = Lift Coefficient*Thrust/Drag Coefficient to calculate the Weight of Body, The Weight of Aircraft for given Coefficients of Lift and Drag is the force exerted by gravity on the mass of the aircraft, it's a crucial parameter in aviation because it affects the aircraft's performance, including its ability to generate lift, maintain altitude, and maneuver, coefficients of lift and drag are dimensionless parameters used in aerodynamics to quantify the lift and drag forces generated by an aircraft's wings or airfoils relative to its size, shape, and flight conditions. Weight of Body is denoted by W_body symbol.

How to calculate Weight of Aircraft for given Coefficients of Lift and Drag using this online calculator? To use this online calculator for Weight of Aircraft for given Coefficients of Lift and Drag, enter Lift Coefficient (C_L), Thrust (T) & Drag Coefficient (C_D) and hit the calculate button. Here is how the Weight of Aircraft for given Coefficients of Lift and Drag calculation can be explained with given input values -> 3.666667 = 1.1*100/0.5.

FAQ

What is Weight of Aircraft for given Coefficients of Lift and Drag?

The Weight of Aircraft for given Coefficients of Lift and Drag is the force exerted by gravity on the mass of the aircraft, it's a crucial parameter in aviation because it affects the aircraft's performance, including its ability to generate lift, maintain altitude, and maneuver, coefficients of lift and drag are dimensionless parameters used in aerodynamics to quantify the lift and drag forces generated by an aircraft's wings or airfoils relative to its size, shape, and flight conditions and is represented as W_body = C_L*T/C_D or Weight of Body = Lift Coefficient*Thrust/Drag Coefficient. The Lift Coefficient is a dimensionless coefficient that relates the lift generated by a lifting body to the fluid density around the body, the fluid velocity and an associated reference area, The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air & Drag Coefficient is a dimensionless quantity that is used to quantify the drag or resistance of an object in a fluid environment, such as air or water.

How to calculate Weight of Aircraft for given Coefficients of Lift and Drag?

The Weight of Aircraft for given Coefficients of Lift and Drag is the force exerted by gravity on the mass of the aircraft, it's a crucial parameter in aviation because it affects the aircraft's performance, including its ability to generate lift, maintain altitude, and maneuver, coefficients of lift and drag are dimensionless parameters used in aerodynamics to quantify the lift and drag forces generated by an aircraft's wings or airfoils relative to its size, shape, and flight conditions is calculated using Weight of Body = Lift Coefficient*Thrust/Drag Coefficient. To calculate Weight of Aircraft for given Coefficients of Lift and Drag, you need Lift Coefficient (C_L), Thrust (T) & Drag Coefficient (C_D). With our tool, you need to enter the respective value for Lift Coefficient, Thrust & Drag Coefficient 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 Lift Coefficient, Thrust & Drag Coefficient. 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 = Thrust*Lift-to-Drag Ratio

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