Coefficient of Lift for given thrust and weight Calculator

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Lift and Drag Requirements

Thrust and Power Requirements

✖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

Formula

`"C"_{"L"} = "W"_{"body"}*"C"_{"D"}/"T"`

Example

`"1.105"="221N"*"0.5"/"100N"`

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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

Vinay Mishra has created this Calculator and 300+ more calculators!

Verified by Maiarutselvan V

PSG College of Technology (PSGCT), Coimbatore

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< 19 Lift and Drag Requirements Calculators

Lift coefficient for given minimum required thrust

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

Zero-lift drag coefficient for given lift coefficient

Go Zero Lift Drag Coefficient = (Thrust/(Dynamic Pressure*Area))-((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing))

Zero-lift drag coefficient at minimum required thrust

Go Zero Lift Drag Coefficient = (Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing)

Lift-induced drag coefficient for given required thrust

Go Coefficient Of Drag Due to Lift = (Thrust/(Dynamic Pressure*Reference Area))-Zero Lift Drag Coefficient

Zero-lift drag coefficient for given required thrust

Go Zero Lift Drag Coefficient = (Thrust/(Dynamic Pressure*Reference Area))-Coefficient Of Drag Due to Lift

Lift for Unaccelerated Flight

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

Coefficient of Drag for given thrust and weight

Go Drag Coefficient = Thrust*Lift Coefficient/Weight of Body

Coefficient of Lift for given thrust and weight

Go Lift Coefficient = Weight of Body*Drag Coefficient/Thrust

Drag for Level and Unaccelerated Flight at Negligible Thrust Angle

Go Drag Force = Dynamic Pressure*Area*Drag Coefficient

Lift for Level and Unaccelerated Flight at Negligible Thrust Angle

Go Lift Force = Dynamic Pressure*Area*Lift Coefficient

Drag for Level and Unaccelerated Flight

Go Drag Force = Thrust*(cos(Thrust angle))

Coefficient of Drag for given thrust-to-weight ratio

Go Drag Coefficient = Lift Coefficient*Thrust-to-Weight Ratio

Coefficient of Lift for given thrust-to-weight ratio

Go Lift Coefficient = Drag Coefficient/Thrust-to-Weight Ratio

Lift-to-drag ratio for given required thrust of aircraft

Go Lift-to-drag Ratio = Weight of Body/Thrust

Freestream Velocity for given total drag force

Go Freestream Velocity = Power/Drag Force

Total drag force for given required power

Go Drag Force = Power/Freestream Velocity

Freestream velocity for given required power

Go Freestream Velocity = Power/Thrust

Coefficient of Drag due to lift for minimum power required

Go Coefficient Of Drag Due to Lift = 3*Zero Lift Drag Coefficient

Zero-lift drag coefficient for minimum power required

Go Zero Lift Drag Coefficient = Coefficient Of Drag Due to Lift/3

Coefficient of Lift for given thrust and weight Formula

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 in a steady, level flight is a number that aerodynamicists use to model all of the complex dependencies of shape, inclination, and some flow conditions on the lift. 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 in a steady, level flight is a number that aerodynamicists use to model all of the complex dependencies of shape, inclination, and some flow conditions on the lift 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 in a steady, level flight is a number that aerodynamicists use to model all of the complex dependencies of shape, inclination, and some flow conditions on the lift 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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