Coefficient of Lift for given thrust and weight Calculator

✖Weight of Body is the force acting on the object due to gravity.ⓘ Weight of Body [W_body]			+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%
✖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 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.ⓘ Coefficient of Lift for given thrust and weight [C_L]

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Coefficient of Lift for given thrust and weight Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

Variables Used

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.
Weight of Body - (Measured in Newton) - Weight of Body is the force acting on the object due to gravity.
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.
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
Drag Coefficient: 0.5 --> No Conversion Required
Thrust: 100 Newton --> 100 Newton No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_L = W_body*C_D/T --> 221*0.5/100

Evaluating ... ...

C_L = 1.105

STEP 3: Convert Result to Output's Unit

1.105 --> No Conversion Required

FINAL ANSWER

1.105 <-- Lift Coefficient

(Calculation completed in 00.004 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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< Lift and Drag Requirements Calculators

Lift for Unaccelerated Flight

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

Drag for Level and Unaccelerated Flight at Negligible Thrust Angle

LaTeX Go Drag Force = Dynamic Pressure*Area*Drag Coefficient

Lift for Level and Unaccelerated Flight at Negligible Thrust Angle

LaTeX Go Lift Force = Dynamic Pressure*Area*Lift Coefficient

Drag for Level and Unaccelerated Flight

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

Coefficient of Lift for given thrust and weight Formula

LaTeX Go

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

How does the thrust-to-weight ratio vary during a flight?

The thrust-to-weight ratio varies continually during a flight. Thrust varies with throttle setting, airspeed, altitude and air temperature. Weight varies with fuel burn and payload changes.

How to Calculate Coefficient of Lift for given thrust and weight?

Coefficient of Lift for given thrust and weight calculator uses Lift Coefficient = Weight of Body*Drag Coefficient/Thrust to calculate the Lift Coefficient, The Coefficient of Lift for given thrust and weight quantifies the lift generated by an airfoil (such as a wing) or an aircraft, it's a dimensionless value that depends on various factors including the shape of the airfoil, the angle of attack, weight and drag. Lift Coefficient is denoted by C_L symbol.

How to calculate Coefficient of Lift for given thrust and weight using this online calculator? To use this online calculator for Coefficient of Lift for given thrust and weight, enter Weight of Body (W_body), Drag Coefficient (C_D) & Thrust (T) and hit the calculate button. Here is how the Coefficient of Lift for given thrust and weight calculation can be explained with given input values -> 66.3 = 221*0.5/100.

FAQ

What is Coefficient of Lift for given thrust and weight?

The Coefficient of Lift for given thrust and weight quantifies the lift generated by an airfoil (such as a wing) or an aircraft, it's a dimensionless value that depends on various factors including the shape of the airfoil, the angle of attack, weight and drag and is represented as C_L = W_body*C_D/T or Lift Coefficient = Weight of Body*Drag Coefficient/Thrust. Weight of Body is the force acting on the object due to gravity, 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 & The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air.

How to calculate Coefficient of Lift for given thrust and weight?

The Coefficient of Lift for given thrust and weight quantifies the lift generated by an airfoil (such as a wing) or an aircraft, it's a dimensionless value that depends on various factors including the shape of the airfoil, the angle of attack, weight and drag is calculated using Lift Coefficient = Weight of Body*Drag Coefficient/Thrust. To calculate Coefficient of Lift for given thrust and weight, you need Weight of Body (W_body), Drag Coefficient (C_D) & Thrust (T). With our tool, you need to enter the respective value for Weight of Body, Drag Coefficient & Thrust 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 Lift Coefficient?

In this formula, Lift Coefficient uses Weight of Body, Drag Coefficient & Thrust. We can use 2 other way(s) to calculate the same, which is/are as follows -

Lift Coefficient = Drag Coefficient/Thrust-to-Weight Ratio
Lift Coefficient = sqrt(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing*((Thrust/(Dynamic Pressure*Area))-Zero Lift Drag Coefficient))

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