Lift in Accelerated Flight Solution

STEP 0: Pre-Calculation Summary
Formula Used
Lift Force = Mass of Aircraft*[g]*cos(Flight Path Angle)+Mass of Aircraft*Velocity^2/Radius of Curvature-Thrust*sin(Thrust Angle)
FL = m*[g]*cos(γ)+m*v^2/Rcurvature-T*sin(σT)
This formula uses 1 Constants, 2 Functions, 7 Variables
Constants Used
[g] - Gravitational acceleration on Earth Value Taken As 9.80665
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)
cos - Cosine of an angle is the ratio of the side adjacent to the angle to the hypotenuse of the triangle., cos(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.
Mass of Aircraft - (Measured in Kilogram) - Mass of Aircraft is the total mass of the plane at any phase of its mission.
Flight Path Angle - (Measured in Radian) - Flight path angle is defined as the angle between horizontal and the flight velocity vector, which describes whether the aircraft is climbing or descending.
Velocity - (Measured in Meter per Second) - Velocity is a vector quantity (it has both magnitude and direction) and is the rate of change of the position of an object with respect to time.
Radius of Curvature - (Measured in Meter) - The Radius of Curvature is the reciprocal of the curvature.
Thrust - (Measured in Newton) - Thrust denotes the force exerted by the engine to propel an aircraft forward.
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
Mass of Aircraft: 20 Kilogram --> 20 Kilogram No Conversion Required
Flight Path Angle: 0.062 Radian --> 0.062 Radian No Conversion Required
Velocity: 60 Meter per Second --> 60 Meter per Second No Conversion Required
Radius of Curvature: 2600 Meter --> 2600 Meter No Conversion Required
Thrust: 700 Newton --> 700 Newton No Conversion Required
Thrust Angle: 0.034 Radian --> 0.034 Radian No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
FL = m*[g]*cos(γ)+m*v^2/Rcurvature-T*sin(σT) --> 20*[g]*cos(0.062)+20*60^2/2600-700*sin(0.034)
Evaluating ... ...
FL = 199.653046007766
STEP 3: Convert Result to Output's Unit
199.653046007766 Newton --> No Conversion Required
FINAL ANSWER
199.653046007766 199.653 Newton <-- Lift Force
(Calculation completed in 00.004 seconds)

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!
Vallurupalli Nageswara Rao Vignana Jyothi Institute of Engineering and Technology (VNRVJIET), Hyderabad
Sai Venkata Phanindra Chary Arendra has verified this Calculator and 300+ more calculators!

16 Climbing Flight Calculators

Velocity in Accelerated Flight
Go Velocity = (Radius of Curvature/Mass of Aircraft*(Lift Force+Thrust*sin(Thrust Angle)-Mass of Aircraft*[g]*cos(Flight Path Angle)))^(1/2)
Lift in Accelerated Flight
Go Lift Force = Mass of Aircraft*[g]*cos(Flight Path Angle)+Mass of Aircraft*Velocity^2/Radius of Curvature-Thrust*sin(Thrust Angle)
Thrust in Accelerated Flight
Go Thrust = (sec(Thrust Angle))*(Drag Force+(Mass of Aircraft*[g]*sin(Flight Path Angle))+(Mass of Aircraft*Acceleration))
Drag in Accelerated Flight
Go Drag Force = Thrust*cos(Thrust Angle)-Mass of Aircraft*[g]*sin(Flight Path Angle)-Mass of Aircraft*Acceleration
Centrifugal Force in Accelerated Flight
Go Centrifugal Force = Lift Force+Thrust*sin(Thrust Angle)-Mass of Aircraft*[g]*cos(Flight Path Angle)
Rate of Climb of Aircraft
Go Rate of Climb = (Power Available-Power Required)/Aircraft weight
Flight path angle at given rate of climb
Go Flight Path Angle = asin(Rate of Climb/Velocity)
Velocity of aircraft at given rate of climb
Go Velocity = Rate of Climb/sin(Flight Path Angle)
Rate of Climb
Go Rate of Climb = Velocity*sin(Flight Path Angle)
Velocity of aircraft for given excess power
Go Velocity = Excess Power/(Thrust-Drag Force)
Thrust available for given excess power
Go Thrust = Drag Force+(Excess Power/Velocity)
Total Drag for given excess power
Go Drag Force = Thrust-(Excess Power/Velocity)
Excess power
Go Excess Power = Velocity*(Thrust-Drag Force)
Weight of aircraft for given excess power
Go Aircraft weight = Excess Power/Rate of Climb
Excess power for given rate of climb
Go Excess Power = Rate of Climb*Aircraft weight
Rate of Climb for given excess power
Go Rate of Climb = Excess Power/Aircraft weight

Lift in Accelerated Flight Formula

Lift Force = Mass of Aircraft*[g]*cos(Flight Path Angle)+Mass of Aircraft*Velocity^2/Radius of Curvature-Thrust*sin(Thrust Angle)
FL = m*[g]*cos(γ)+m*v^2/Rcurvature-T*sin(σT)

What happens to the lift if thrust increase?

If the thrust of an aircraft is increased, the aircraft will accelerate and the velocity will increase.

How to Calculate Lift in Accelerated Flight?

Lift in Accelerated Flight calculator uses Lift Force = Mass of Aircraft*[g]*cos(Flight Path Angle)+Mass of Aircraft*Velocity^2/Radius of Curvature-Thrust*sin(Thrust Angle) to calculate the Lift Force, The Lift in Accelerated Flight is a function of the weight of aircraft, flight velocity, the thrust of aircraft, thrust angle, flight path angle, and radius of curvature of the curved path. Lift Force is denoted by FL symbol.

How to calculate Lift in Accelerated Flight using this online calculator? To use this online calculator for Lift in Accelerated Flight, enter Mass of Aircraft (m), Flight Path Angle (γ), Velocity (v), Radius of Curvature (Rcurvature), Thrust (T) & Thrust Angle T) and hit the calculate button. Here is how the Lift in Accelerated Flight calculation can be explained with given input values -> 4971.961 = 20*[g]*cos(0.062)+20*60^2/radius_of_curvature_eom-700*sin(0.034).

FAQ

What is Lift in Accelerated Flight?
The Lift in Accelerated Flight is a function of the weight of aircraft, flight velocity, the thrust of aircraft, thrust angle, flight path angle, and radius of curvature of the curved path and is represented as FL = m*[g]*cos(γ)+m*v^2/Rcurvature-T*sin(σT) or Lift Force = Mass of Aircraft*[g]*cos(Flight Path Angle)+Mass of Aircraft*Velocity^2/Radius of Curvature-Thrust*sin(Thrust Angle). Mass of Aircraft is the total mass of the plane at any phase of its mission, Flight path angle is defined as the angle between horizontal and the flight velocity vector, which describes whether the aircraft is climbing or descending, Velocity is a vector quantity (it has both magnitude and direction) and is the rate of change of the position of an object with respect to time, The Radius of Curvature is the reciprocal of the curvature, Thrust denotes the force exerted by the engine to propel an aircraft forward & Thrust angle is defined as the angle between thrust vector and flight path (or flight velocity) direction.
How to calculate Lift in Accelerated Flight?
The Lift in Accelerated Flight is a function of the weight of aircraft, flight velocity, the thrust of aircraft, thrust angle, flight path angle, and radius of curvature of the curved path is calculated using Lift Force = Mass of Aircraft*[g]*cos(Flight Path Angle)+Mass of Aircraft*Velocity^2/Radius of Curvature-Thrust*sin(Thrust Angle). To calculate Lift in Accelerated Flight, you need Mass of Aircraft (m), Flight Path Angle (γ), Velocity (v), Radius of Curvature (Rcurvature), Thrust (T) & Thrust Angle T). With our tool, you need to enter the respective value for Mass of Aircraft, Flight Path Angle, Velocity, Radius of Curvature, Thrust & Thrust Angle and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.
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