Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
Vinay Mishra has created this Calculator and 300+ more calculators!
Shikha Maurya
Indian Institute of Technology (IIT), Bombay
Shikha Maurya has verified this Calculator and 100+ more calculators!

11 Other formulas that you can solve using the same Inputs

Minimum Thrust required for given weight
Thrust of an aircraft=(Dynamic Pressure*Reference Area*Zero-lift drag coefficient)+((Weight^2)/(Dynamic Pressure*Reference Area*pi*Oswald efficiency factor*Aspect Ratio of a wing)) GO
Power required at sea-level condition
Power required at sea-level=sqrt(2*(Weight^3)*(Drag Coefficient^2)/([Std-Air-Density-Sea]*Reference Area*(lift coefficient^3))) GO
Velocity at sea-level condition
Velocity at sea-level=sqrt(2*Weight/([Std-Air-Density-Sea]*Reference Area*lift coefficient)) GO
Power required for given aerodynamic coefficients
Power=Weight*Freestream Velocity*Drag Coefficient/lift coefficient GO
Coefficient of Drag for given thrust and weight
Drag Coefficient=Thrust of an aircraft*lift coefficient/Weight GO
Coefficient of Lift for given thrust and weight
lift coefficient=Weight*Drag Coefficient/Thrust of an aircraft GO
Thrust for given coefficients of lift and drag
Thrust of an aircraft=Drag Coefficient*Weight/lift coefficient GO
Lift for an unaccelerated flight
Lift force=Weight-(Thrust of an aircraft*sin(Thrust angle)) GO
Thrust angle for an unaccelerated flight for given lift
Thrust angle=asin((Weight-Lift force)/Thrust of an aircraft) GO
Thrust required for given Lift-to-drag ratio
Thrust of an aircraft=Weight/Lift-to-drag ratio GO
Lift-to-drag ratio for given required thrust
Lift-to-drag ratio=Weight/Thrust of an aircraft 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 force for a body moving in a fluid of certain density
Lift force=lift coefficient*Reference Area*Density*(Velocity^2)/2 GO
Lift for an unaccelerated flight
Lift force=Weight-(Thrust of an aircraft*sin(Thrust angle)) 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 acting on aircraft during ground roll Formula

Lift force=Weight-(Rolling Resistance/Coefficient of Rolling Friction)
L=W-(R/μ<sub>r</sub>)
More formulas
Resistance force during ground roll GO
Coefficient of rolling friction during ground roll GO
Weight of aircraft during ground roll GO
Ground effect factor GO
Drag during ground effect GO
Liftoff velocity for given stall velocity GO
Stall velocity for given liftoff velocity GO
Liftoff velocity for given weight GO
Stall velocity for given weight GO
Maximum Lift coefficient for given stall velocity GO
Maximum Lift coefficient for given liftoff velocity GO
Liftoff distance GO
Thrust for given liftoff distance GO

What should flaps be at takeoff?

Aircraft use takeoff flap settings that are usually between 5-15 degrees (most jets use leading-edge slats as well).

How to Calculate Lift acting on aircraft during ground roll?

Lift acting on aircraft during ground roll calculator uses Lift force=Weight-(Rolling Resistance/Coefficient of Rolling Friction) to calculate the Lift force, The Lift acting on aircraft during ground roll is equal to the weight of the aircraft at that instant minus the ratio of rolling resistance (due to rolling friction between the tires and the ground) and coefficient of rolling friction. Lift force and is denoted by L symbol.

How to calculate Lift acting on aircraft during ground roll using this online calculator? To use this online calculator for Lift acting on aircraft during ground roll, enter Weight (W), Rolling Resistance (R) and Coefficient of Rolling Friction r) and hit the calculate button. Here is how the Lift acting on aircraft during ground roll calculation can be explained with given input values -> 50 = 100-(5/0.1).

FAQ

What is Lift acting on aircraft during ground roll?
The Lift acting on aircraft during ground roll is equal to the weight of the aircraft at that instant minus the ratio of rolling resistance (due to rolling friction between the tires and the ground) and coefficient of rolling friction and is represented as L=W-(R/μr) or Lift force=Weight-(Rolling Resistance/Coefficient of Rolling Friction). Weight is a vector quantity and defined as the product of mass and acceleration acting on that mass, Rolling Resistance (or Rolling friction) is the force resisting the motion of a rolling body on a surface and Coefficient of Rolling Friction is the ratio of the force of rolling friction to the total weight of the object.
How to calculate Lift acting on aircraft during ground roll?
The Lift acting on aircraft during ground roll is equal to the weight of the aircraft at that instant minus the ratio of rolling resistance (due to rolling friction between the tires and the ground) and coefficient of rolling friction is calculated using Lift force=Weight-(Rolling Resistance/Coefficient of Rolling Friction). To calculate Lift acting on aircraft during ground roll, you need Weight (W), Rolling Resistance (R) and Coefficient of Rolling Friction r). With our tool, you need to enter the respective value for Weight, Rolling Resistance and Coefficient of Rolling Friction 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, Rolling Resistance and Coefficient of Rolling Friction. 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=Weight-(Thrust of an aircraft*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/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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