Thrust for given 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%
✖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]			+10% -10%

✖The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air.ⓘ Thrust for given liftoff distance [T]

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Formula

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Thrust for given liftoff distance

Formula

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

Example

`"0.102094N"=1.44*(("60.34N")^2)/("[g]"*"1.225kg/m³"*"5.08m²"*"1.65"*"510m")`

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Thrust for given liftoff distance Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

Constants Used

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

Variables Used

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.
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.
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.

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
Liftoff Distance: 510 Meter --> 510 Meter No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

T = 1.44*(W^2)/([g]*ρ_∞*S*C_L,max*s_LO) --> 1.44*(60.34^2)/([g]*1.225*5.08*1.65*510)

Evaluating ... ...

T = 0.102093597373326

STEP 3: Convert Result to Output's Unit

0.102093597373326 Newton --> No Conversion Required

FINAL ANSWER

0.102093597373326 ≈ 0.102094 Newton <-- Thrust of an aircraft

(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

Thrust for given liftoff distance Formula

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

Can planes stop in the air?

No. A plane doesn't stop in midair. Planes need to keep moving forward to remain in the air (unless they are VTOL capable).

How to Calculate Thrust for given liftoff distance?

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

How to calculate Thrust for given liftoff distance using this online calculator? To use this online calculator for Thrust for given liftoff distance, enter Weight Newton (W), Freestream density (ρ_∞), Reference Area (S), Maximum Lift Coefficient (C_L,max) & Liftoff Distance (s_LO) and hit the calculate button. Here is how the Thrust for given liftoff distance calculation can be explained with given input values -> 0.001795 = 1.44*(60.34^2)/([g]*1.225*5.08*1.65*510).

FAQ

What is Thrust for given liftoff distance?

The Thrust for given liftoff distance is a function of weight, altitude, maximum coefficient of lift (ignoring drag and rolling resistance as compared to thrust) and is represented as T = 1.44*(W^2)/([g]*ρ_∞*S*C_L,max*s_LO) or Thrust of an aircraft = 1.44*(Weight Newton^2)/([g]*Freestream density*Reference Area*Maximum Lift Coefficient*Liftoff Distance). 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 & 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.

How to calculate Thrust for given liftoff distance?

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