Lift for an unaccelerated flight Calculator

Category	Physics ↺
Physics	Flight Stability and Control ↺
Flight-Stability-And-Control	Airplane Performance ↺
Airplane-Performance	Equations of Motion ↺

✖Weight is a vector quantity and defined as the product of mass and acceleration acting on that massⓘ Weight [W]			+10% -10%
✖The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air.ⓘ Thrust of an aircraft [T]			+10% -10%
✖Thrust angle is defined as the angle between thrust vector and flight path (or flight velocity) direction.ⓘ Thrust angle [α_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 an unaccelerated flight [L]

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Vinay Mishra

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

Vinay Mishra has created this Calculator and 200+ more calculators!

Sai Venkata Phanindra Chary Arendra

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

Sai Venkata Phanindra Chary Arendra has verified this Calculator and 100+ more calculators!

< 11 Other formulas that you can solve using the same Inputs

Velocity in an accelerated flight

Velocity=((Radius of Curvature/Mass)*(Lift force+(Thrust force*sin(Thrust angle))-(Mass*[g]*cos(Flight path angle))))^(1/2) GO

Lift in an accelerated flight

Lift force=(Mass*[g]*cos(Flight path angle))+(Mass*(Velocity^2)/Radius of Curvature)-(Thrust force*sin(Thrust angle)) GO

Thrust in an accelerated flight

Thrust of an aircraft=(sec(Thrust angle))*(Drag Force+(Mass*[g]*sin(Flight path angle))+(Mass*Acceleration)) GO

Drag in an accelerated flight

Drag Force=(Thrust of an aircraft*cos(Thrust angle))-(Mass*[g]*(sin(Flight path angle)))-(Mass*Acceleration) GO

Centrifugal Force in an accelerated flight

Centrifugal force=Lift force+(Thrust force*sin(Thrust angle))-(Mass*[g]*cos(Flight path angle)) GO

Weight of aircraft for given coefficients of lift and drag

Weight=lift coefficient*Thrust of an aircraft/Drag Coefficient GO

Thrust for given coefficients of lift and drag

Thrust of an aircraft=Drag Coefficient*Weight/lift coefficient GO

Thrust angle for an unaccelerated flight for given lift

Thrust angle=asin((Weight-Lift force)/Thrust of an aircraft) GO

Weight of aircraft in level, unaccelerated flight

Weight=Lift force+(Thrust of an aircraft*sin(Thrust angle)) GO

Thrust for a level, unaccelerated flight

Thrust of an aircraft=Drag Force/(cos(Thrust angle)) GO

Drag for a level, unaccelerated flight

Drag Force=Thrust of an aircraft*(cos(Thrust angle)) GO

< 11 Other formulas that calculate the same Output

Lift in an accelerated flight

Lift force=(Mass*[g]*cos(Flight path angle))+(Mass*(Velocity^2)/Radius of Curvature)-(Thrust force*sin(Thrust angle)) GO

Forces acting Perpendicular to the body on the flight path

Lift force=Weight*cos(Angle of Inclination)-Mass*((Velocity^2)/Radius) GO

Lift acting on aircraft during ground roll

Lift force=Weight-(Rolling Resistance/Coefficient of Rolling Friction) GO

Lift force for a body moving in a fluid of certain density

Lift force=lift coefficient*Reference Area*Density*(Velocity^2)/2 GO

Lift for a level, unaccelerated flight at negligible thrust angle

Lift force=Dynamic Pressure*Area*lift coefficient GO

Lift Force

Lift force=lift coefficient*Dynamic Pressure*Area GO

Total Lift of wing-tail combination

Lift force=Lift due to wing+Lift due to tail GO

Lift force with angle of attack

Lift force=Drag Force*cot(Angle of attack) GO

Lift for given glide angle

Lift force=Drag Force/tan(Glide angle) GO

Lift during level turn

Lift force=Weight/cos(Bank angle) GO

Lift for a given load factor

Lift force=Load factor*Weight GO

Lift for an unaccelerated flight Formula

Lift force=Weight-(Thrust of an aircraft*sin(Thrust angle))
L=W-(T*sin(α<sub>T</sub>))

More formulas

Thrust in an accelerated flight GO

Drag in an accelerated flight GO

Lift in an accelerated flight GO

Centrifugal Force in an accelerated flight GO

Velocity in an accelerated flight GO

Thrust for a level, unaccelerated flight GO

Drag for a level, unaccelerated flight GO

Thrust angle for an unaccelerated flight for given drag GO

Weight of aircraft in level, unaccelerated flight GO

Thrust angle for an unaccelerated flight for given lift GO

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 an unaccelerated flight?

Lift for an unaccelerated flight calculator uses Lift force=Weight-(Thrust of an aircraft*sin(Thrust angle)) to calculate the Lift force, The Lift for an unaccelerated flight is the difference in weight and sine component of the thrust of an aircraft. Lift force and is denoted by L symbol.

How to calculate Lift for an unaccelerated flight using this online calculator? To use this online calculator for Lift for an unaccelerated flight, enter Weight (W), Thrust of an aircraft (T) and Thrust angle (α_T) and hit the calculate button. Here is how the Lift for an unaccelerated flight calculation can be explained with given input values -> 96.50071 = 100-(100*sin(2.00535228295826)) .

FAQ

What is Lift for an unaccelerated flight?

The Lift for an unaccelerated flight is the difference in weight and sine component of the thrust of an aircraft and is represented as L=W-(T*sin(α_T)) or Lift force=Weight-(Thrust of an aircraft*sin(Thrust angle)) . Weight is a vector quantity and defined as the product of mass and acceleration acting on that mass, The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air and Thrust angle is defined as the angle between thrust vector and flight path (or flight velocity) direction.

How to calculate Lift for an unaccelerated flight?

The Lift for an unaccelerated flight is the difference in weight and sine component of the thrust of an aircraft is calculated using Lift force=Weight-(Thrust of an aircraft*sin(Thrust angle)) . To calculate Lift for an unaccelerated flight, you need Weight (W), Thrust of an aircraft (T) and Thrust angle (α_T). With our tool, you need to enter the respective value for Weight, Thrust of an aircraft and 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, Thrust of an aircraft and Thrust angle. We can use 11 other way(s) to calculate the same, which is/are as follows -

Lift force=lift coefficient*Dynamic Pressure*Area
Lift force=Weight*cos(Angle of Inclination)-Mass*((Velocity^2)/Radius)
Lift force=(Mass*[g]*cos(Flight path angle))+(Mass*(Velocity^2)/Radius of Curvature)-(Thrust force*sin(Thrust angle))
Lift force=Dynamic Pressure*Area*lift coefficient
Lift force=Drag Force*cot(Angle of attack)
Lift force=Drag Force/tan(Glide angle)
Lift force=Weight-(Rolling Resistance/Coefficient of Rolling Friction)
Lift force=Weight/cos(Bank angle)
Lift force=Load factor*Weight
Lift force=Lift due to wing+Lift due to tail
Lift force=lift coefficient*Reference Area*Density*(Velocity^2)/2

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