Lift for Unaccelerated Flight Calculator

✖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 \cdot \sin (σ T)

Example

220 N = 221 N - 100 N \cdot \sin (0.01 rad)

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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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< Lift and Drag Requirements Calculators

Lift for Unaccelerated Flight

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

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)

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 refers to the aerodynamic force generated by an aircraft's wings when the aircraft is maintaining a constant velocity without any change in speed or direction, in unaccelerated flight, the lift force produced by the wings exactly balances the weight of the aircraft, allowing it to maintain level flight at a steady altitude. 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 refers to the aerodynamic force generated by an aircraft's wings when the aircraft is maintaining a constant velocity without any change in speed or direction, in unaccelerated flight, the lift force produced by the wings exactly balances the weight of the aircraft, allowing it to maintain level flight at a steady altitude 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 refers to the aerodynamic force generated by an aircraft's wings when the aircraft is maintaining a constant velocity without any change in speed or direction, in unaccelerated flight, the lift force produced by the wings exactly balances the weight of the aircraft, allowing it to maintain level flight at a steady altitude 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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