Liftoff distance Calculator

Category	Physics ↺
Physics	Flight Stability and Control ↺
Flight-Stability-And-Control	Airplane Performance ↺
Airplane-Performance	Takeoff Performance ↺

✖Weight is a vector quantity and defined as the product of mass and acceleration acting on that massⓘ Weight [W]			+10% -10%
✖Freestream density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitudeⓘ Freestream density [ρ_∞]			+10% -10%
✖The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area.ⓘ Reference Area [S]			+10% -10%
✖Maximum Lift Coefficient is defined as the lift coefficient of the airfoil at stalling angle of attackⓘ Maximum Lift Coefficient [C_L,max]			+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%

✖Liftoff Distance is the portion of the takeoff procedure during which the airplane is accelerated from a standstill to an airspeed that provides sufficient lift for it to become airborneⓘ Liftoff distance [s_LO]

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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!

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

Drag in an accelerated flight

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

Weight of aircraft for given coefficients of lift and drag

Weight=lift coefficient*Thrust of an aircraft/Drag 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

Weight of aircraft in level, unaccelerated flight

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

Drag for a level, unaccelerated flight

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

Weight of aircraft for given Lift-to-drag ratio

Weight=Thrust of an aircraft*Lift-to-drag ratio GO

Thrust required for given Lift-to-drag ratio

Thrust of an aircraft=Weight/Lift-to-drag ratio GO

Liftoff distance Formula

Liftoff Distance=1.44*(Weight^2)/([g]*Freestream density*Reference Area*Maximum Lift Coefficient*Thrust of an aircraft)
sLO=1.44*(W^2)/([g]*ρ∞*S*CL,max*T)

More formulas

Resistance force during ground roll GO

Coefficient of rolling friction during ground roll GO

Weight of aircraft during ground roll GO

Lift acting on 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

Thrust for given liftoff distance GO

What is the difference between lift off and take off?

As per aviation terminology, take-off is the distance covered by an airplane from the start of take-off roll to the point the airplane is 1500 feet above the take-off surface. Lift off is when the airplane becomes airborne, that is when the main wheels lift off the ground.

How to Calculate Liftoff distance?

Liftoff distance calculator uses Liftoff Distance=1.44*(Weight^2)/([g]*Freestream density*Reference Area*Maximum Lift Coefficient*Thrust of an aircraft) to calculate the Liftoff Distance, The Liftoff distance is a function of weight, altitude, maximum coefficient of lift, and thrust of the aircraft (ignoring drag and rolling resistance). Liftoff Distance and is denoted by s_LO symbol.

How to calculate Liftoff distance using this online calculator? To use this online calculator for Liftoff distance, enter Weight (W), Freestream density (ρ_∞), Reference Area (S), Maximum Lift Coefficient (C_L,max) and Thrust of an aircraft (T) and hit the calculate button. Here is how the Liftoff distance calculation can be explained with given input values -> 1.452954 = 1.44*(100^2)/([g]*1.225*5*1.65*100).

FAQ

What is Liftoff distance?

The Liftoff distance is a function of weight, altitude, maximum coefficient of lift, and thrust of the aircraft (ignoring drag and rolling resistance) and is represented as s_LO=1.44*(W^2)/([g]*ρ_∞*S*C_L,max*T) or Liftoff Distance=1.44*(Weight^2)/([g]*Freestream density*Reference Area*Maximum Lift Coefficient*Thrust of an aircraft). Weight is a vector quantity and defined as the product of mass and acceleration acting on that mass, Freestream density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude, The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area, Maximum Lift Coefficient is defined as the lift coefficient of the airfoil at stalling angle of attack and The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air.

How to calculate Liftoff distance?

The Liftoff distance is a function of weight, altitude, maximum coefficient of lift, and thrust of the aircraft (ignoring drag and rolling resistance) is calculated using Liftoff Distance=1.44*(Weight^2)/([g]*Freestream density*Reference Area*Maximum Lift Coefficient*Thrust of an aircraft). To calculate Liftoff distance, you need Weight (W), Freestream density (ρ_∞), Reference Area (S), Maximum Lift Coefficient (C_L,max) and Thrust of an aircraft (T). With our tool, you need to enter the respective value for Weight, Freestream density, Reference Area, Maximum Lift Coefficient and Thrust of an aircraft 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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