Lift for Unaccelerated Flight 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%
✖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%
✖Thrust angle is defined as the angle between thrust vector and flight path (or flight velocity) direction.ⓘ Thrust angle [σ_T]			+10% -10%

✖The Lift Force, lifting force or simply lift is the sum of all the forces on a body that force it to move perpendicular to the direction of flow.ⓘ Lift for Unaccelerated Flight [F_L]

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Formula

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Lift for Unaccelerated Flight

Formula

`"F"_{"L"} = "W"_{"body"}-"T"*sin("σ"_{"T"})`

Example

`"220N"="221N"-"100N"*sin("0.01rad")`

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Lift for Unaccelerated Flight Solution

STEP 0: Pre-Calculation Summary

Formula Used

Lift Force = Weight of Body-Thrust*sin(Thrust angle)
F_L = W_body-T*sin(σ_T)
This formula uses 1 Functions, 4 Variables

Functions Used

sin - Sine is a trigonometric function that describes the ratio of the length of the opposite side of a right triangle to the length of the hypotenuse., sin(Angle)

Variables Used

Lift Force - (Measured in Newton) - The Lift Force, lifting force or simply lift is the sum of all the forces on a body that force it to move perpendicular to the direction of flow.
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.
Thrust angle - (Measured in Radian) - Thrust angle is defined as the angle between thrust vector and flight path (or flight velocity) direction.

STEP 1: Convert Input(s) to Base Unit

Weight of Body: 221 Newton --> 221 Newton No Conversion Required
Thrust: 100 Newton --> 100 Newton No Conversion Required
Thrust angle: 0.01 Radian --> 0.01 Radian No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

F_L = W_body-T*sin(σ_T) --> 221-100*sin(0.01)

Evaluating ... ...

F_L = 220.000016666583

STEP 3: Convert Result to Output's Unit

220.000016666583 Newton --> No Conversion Required

FINAL ANSWER

220.000016666583 ≈ 220 Newton <-- Lift Force

(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 Sai Venkata Phanindra Chary Arendra

Vallurupalli Nageswara Rao Vignana Jyothi Institute of Engineering and Technology (VNRVJIET), Hyderabad

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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

Lift for Unaccelerated Flight Formula

Lift Force = Weight of Body-Thrust*sin(Thrust angle)
F_L = W_body-T*sin(σ_T)

What is the lift force of an airplane?

Lift is a mechanical aerodynamic force that directly opposes the weight of an airplane and holds the airplane in the air.

How to Calculate Lift for Unaccelerated Flight?

Lift for Unaccelerated Flight calculator uses Lift Force = Weight of Body-Thrust*sin(Thrust angle) to calculate the Lift Force, The Lift for Unaccelerated Flight is the difference in weight and sine component of the thrust of an aircraft. Lift Force is denoted by F_L symbol.

How to calculate Lift for Unaccelerated Flight using this online calculator? To use this online calculator for Lift for Unaccelerated Flight, enter Weight of Body (W_body), Thrust (T) & Thrust angle (σ_T) and hit the calculate button. Here is how the Lift for Unaccelerated Flight calculation can be explained with given input values -> 220 = 221-100*sin(0.01).

FAQ

What is Lift for Unaccelerated Flight?

The Lift for Unaccelerated Flight is the difference in weight and sine component of the thrust of an aircraft and is represented as F_L = W_body-T*sin(σ_T) or Lift Force = Weight of Body-Thrust*sin(Thrust angle). Weight of Body is the force acting on the object due to gravity, The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air & Thrust angle is defined as the angle between thrust vector and flight path (or flight velocity) direction.

How to calculate Lift for Unaccelerated Flight?

The Lift for Unaccelerated Flight is the difference in weight and sine component of the thrust of an aircraft is calculated using Lift Force = Weight of Body-Thrust*sin(Thrust angle). To calculate Lift for Unaccelerated Flight, you need Weight of Body (W_body), Thrust (T) & Thrust angle (σ_T). With our tool, you need to enter the respective value for Weight of Body, Thrust & Thrust angle 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 Force?

In this formula, Lift Force uses Weight of Body, Thrust & Thrust angle. We can use 1 other way(s) to calculate the same, which is/are as follows -

Lift Force = Dynamic Pressure*Area*Lift Coefficient

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