Liftoff distance Calculator

✖Weight Newton 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%
✖Aircraft Thrust is defined as the force generated through propulsion engines that move an aircraft through the air.ⓘ Aircraft Thrust [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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Liftoff distance Solution

STEP 0: Pre-Calculation Summary

Formula Used

Liftoff Distance = 1.44*(Weight^2)/([g]*Freestream Density*Reference Area*Maximum Lift Coefficient*Aircraft Thrust)
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 - (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.
Aircraft Thrust - (Measured in Newton) - Aircraft Thrust 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: 60.5 Newton --> 60.5 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: 0.000885 --> No Conversion Required
Aircraft Thrust: 186.5 Newton --> 186.5 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*(60.5^2)/([g]*1.225*5.08*0.000885*186.5)

Evaluating ... ...

s_LO = 523.275809231745

STEP 3: Convert Result to Output's Unit

523.275809231745 Meter --> No Conversion Required

FINAL ANSWER

523.275809231745 ≈ 523.2758 Meter <-- Liftoff Distance

(Calculation completed in 00.004 seconds)

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Created by Vinay Mishra

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

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Verified by Shikha Maurya

Indian Institute of Technology (IIT), Bombay

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< Take Off Calculators

Coefficient of rolling friction during ground roll

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Lift acting on aircraft during ground roll

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

Weight of aircraft during ground roll

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

Resistance force during ground roll

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

Liftoff distance Formula

LaTeX Go

Liftoff Distance = 1.44*(Weight^2)/([g]*Freestream Density*Reference Area*Maximum Lift Coefficient*Aircraft Thrust)
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^2)/([g]*Freestream Density*Reference Area*Maximum Lift Coefficient*Aircraft Thrust) to calculate the Liftoff Distance, Liftoff Distance is a measure of the distance required by an aircraft to take off from the ground, calculated by considering the weight tolerance, freestream density, reference area, maximum lift coefficient, and thrust of the aircraft, providing a critical parameter for aircraft design and performance evaluation. 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 (W), Freestream Density (ρ_∞), Reference Area (S), Maximum Lift Coefficient (C_L,max) & Aircraft Thrust (T) and hit the calculate button. Here is how the Liftoff distance calculation can be explained with given input values -> 975909.4 = 1.44*(60.5^2)/([g]*1.225*5.08*0.000885*186.5).

FAQ

What is Liftoff distance?

Liftoff Distance is a measure of the distance required by an aircraft to take off from the ground, calculated by considering the weight tolerance, freestream density, reference area, maximum lift coefficient, and thrust of the aircraft, providing a critical parameter for aircraft design and performance evaluation 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*Aircraft Thrust). 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 & Aircraft Thrust is defined as the force generated through propulsion engines that move an aircraft through the air.

How to calculate Liftoff distance?

Liftoff Distance is a measure of the distance required by an aircraft to take off from the ground, calculated by considering the weight tolerance, freestream density, reference area, maximum lift coefficient, and thrust of the aircraft, providing a critical parameter for aircraft design and performance evaluation is calculated using Liftoff Distance = 1.44*(Weight^2)/([g]*Freestream Density*Reference Area*Maximum Lift Coefficient*Aircraft Thrust). To calculate Liftoff distance, you need Weight (W), Freestream Density (ρ_∞), Reference Area (S), Maximum Lift Coefficient (C_L,max) & Aircraft Thrust (T). With our tool, you need to enter the respective value for Weight, Freestream Density, Reference Area, Maximum Lift Coefficient & Aircraft Thrust 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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