Liftoff distance Calculator

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✖Weight Newton is a vector quantity and defined as the product of mass and acceleration acting on that mass.ⓘ Weight Newton [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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Formula

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Liftoff distance

Formula

`"s"_{"LO"} = 1.44*("W"^2)/("[g]"*"ρ"_{"∞"}*"S"*"C"_{"L,max"}*"T")`

Example

`"0.520677m"=1.44*(("60.34N")^2)/("[g]"*"1.225kg/m³"*"5.08m²"*"1.65"*"100N")`

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Liftoff distance Solution

STEP 0: Pre-Calculation Summary

Formula Used

Liftoff Distance = 1.44*(Weight Newton^2)/([g]*Freestream density*Reference Area*Maximum Lift Coefficient*Thrust of an aircraft)
s_LO = 1.44*(W^2)/([g]*ρ_∞*S*C_L,max*T)
This formula uses 1 Constants, 6 Variables

Constants Used

[g] - Gravitational acceleration on Earth Value Taken As 9.80665

Variables Used

Liftoff Distance - (Measured in Meter) - 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.
Weight Newton - (Measured in Newton) - Weight Newton is a vector quantity and defined as the product of mass and acceleration acting on that mass.
Freestream density - (Measured in Kilogram per Cubic Meter) - Freestream density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude.
Reference Area - (Measured in Square Meter) - 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 - Maximum Lift Coefficient is defined as the lift coefficient of the airfoil at stalling angle of attack.
Thrust of an aircraft - (Measured in Newton) - The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air.

STEP 1: Convert Input(s) to Base Unit

Weight Newton: 60.34 Newton --> 60.34 Newton No Conversion Required
Freestream density: 1.225 Kilogram per Cubic Meter --> 1.225 Kilogram per Cubic Meter No Conversion Required
Reference Area: 5.08 Square Meter --> 5.08 Square Meter No Conversion Required
Maximum Lift Coefficient: 1.65 --> No Conversion Required
Thrust of an aircraft: 100 Newton --> 100 Newton No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

s_LO = 1.44*(W^2)/([g]*ρ_∞*S*C_L,max*T) --> 1.44*(60.34^2)/([g]*1.225*5.08*1.65*100)

Evaluating ... ...

s_LO = 0.520677346603961

STEP 3: Convert Result to Output's Unit

0.520677346603961 Meter --> No Conversion Required

FINAL ANSWER

0.520677346603961 ≈ 0.520677 Meter <-- Liftoff Distance

(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 Shikha Maurya

Indian Institute of Technology (IIT), Bombay

Shikha Maurya has verified this Calculator and 200+ more calculators!

< 15 Take-Off Calculators

Take Off Ground Run

Go Takeoff Ground Run = Weight Of Aircraft/(2*[g])*int((2*Velocity of Aircraft)/(Thrust Force-Drag Force-Reference Of Rolling Resistance Coefficient*(Weight Of Aircraft-Lift Force)),x,0,Aircraft Lift Off Speed)

Drag during ground effect

Go Drag Force = (Parasite Drag coefficient+(((Lift Coefficient^2)*Ground effect factor)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)))*(0.5*Freestream density*(Flight Velocity^2)*Reference Area)

Thrust for given liftoff distance

Go Thrust of an aircraft = 1.44*(Weight Newton^2)/([g]*Freestream density*Reference Area*Maximum Lift Coefficient*Liftoff Distance)

Liftoff distance

Go Liftoff Distance = 1.44*(Weight Newton^2)/([g]*Freestream density*Reference Area*Maximum Lift Coefficient*Thrust of an aircraft)

Liftoff velocity for given weight

Go Liftoff velocity = 1.2*(sqrt((2*Weight Newton)/(Freestream density*Reference Area*Maximum Lift Coefficient)))

Stall velocity for given weight

Go Stall Velocity = sqrt((2*Weight Newton)/(Freestream density*Reference Area*Maximum Lift Coefficient))

Maximum Lift coefficient for given liftoff velocity

Go Maximum Lift Coefficient = 2.88*Weight Newton/(Freestream density*Reference Area*(Liftoff velocity^2))

Ground effect factor

Go Ground effect factor = ((16*Height from Ground/Wingspan)^2)/(1+((16*Height from Ground/Wingspan)^2))

Maximum Lift coefficient for given stall velocity

Go Maximum Lift Coefficient = 2*Weight Newton/(Freestream density*Reference Area*(Stall Velocity^2))

Coefficient of rolling friction during ground roll

Go Coefficient of Rolling Friction = Rolling Resistance/(Weight Newton-Lift Force)

Lift acting on aircraft during ground roll

Go Lift Force = Weight Newton-(Rolling Resistance/Coefficient of Rolling Friction)

Weight of aircraft during ground roll

Go Weight Newton = (Rolling Resistance/Coefficient of Rolling Friction)+Lift Force

Resistance force during ground roll

Go Rolling Resistance = Coefficient of Rolling Friction*(Weight Newton-Lift Force)

Liftoff velocity for given stall velocity

Go Liftoff velocity = 1.2*Stall Velocity

Stall velocity for given liftoff velocity

Go Stall Velocity = Liftoff velocity/1.2

Liftoff distance Formula

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

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 Newton^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 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 Newton (W), Freestream density (ρ_∞), Reference Area (S), Maximum Lift Coefficient (C_L,max) & Thrust of an aircraft (T) and hit the calculate button. Here is how the Liftoff distance calculation can be explained with given input values -> 0.009152 = 1.44*(60.34^2)/([g]*1.225*5.08*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 Newton^2)/([g]*Freestream density*Reference Area*Maximum Lift Coefficient*Thrust of an aircraft). Weight Newton 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 & 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 Newton^2)/([g]*Freestream density*Reference Area*Maximum Lift Coefficient*Thrust of an aircraft). To calculate Liftoff distance, you need Weight Newton (W), Freestream density (ρ_∞), Reference Area (S), Maximum Lift Coefficient (C_L,max) & Thrust of an aircraft (T). With our tool, you need to enter the respective value for Weight Newton, Freestream density, Reference Area, Maximum Lift Coefficient & 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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