Thrust for given 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%
✖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%

✖Aircraft Thrust 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 \cdot \frac{W^{2}}{[g] \cdot ρ ∞ \cdot S \cdot C L,max \cdot s LO}

Example

186.5984 N = 1.44 \cdot \frac{{60.5 N}^{2}}{[g] \cdot 1.225 kg/m³ \cdot 5.08 m² \cdot 0.000885 \cdot 523 m}

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Thrust for given liftoff distance Solution

STEP 0: Pre-Calculation Summary

Formula Used

Aircraft Thrust = 1.44*(Weight^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

Aircraft Thrust - (Measured in Newton) - Aircraft Thrust is defined as the force generated through propulsion engines that move an aircraft through the air.
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.
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: 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
Liftoff Distance: 523 Meter --> 523 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*(60.5^2)/([g]*1.225*5.08*0.000885*523)

Evaluating ... ...

T = 186.598352622793

STEP 3: Convert Result to Output's Unit

186.598352622793 Newton --> No Conversion Required

FINAL ANSWER

186.598352622793 ≈ 186.5984 Newton <-- Aircraft Thrust

(Calculation completed in 00.020 seconds)

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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

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< Take Off Calculators

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

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Thrust for given liftoff distance Formula

Aircraft Thrust = 1.44*(Weight^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 Aircraft Thrust = 1.44*(Weight^2)/([g]*Freestream Density*Reference Area*Maximum Lift Coefficient*Liftoff Distance) to calculate the Aircraft Thrust, Thrust for Given Liftoff Distance is a measure of the minimum thrust required for an aircraft to take off from a given distance, considering the aircraft's weight, free stream density, reference area, maximum lift coefficient, and liftoff distance, ensuring a safe and efficient departure. Aircraft Thrust 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 (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 -> 186.5984 = 1.44*(60.5^2)/([g]*1.225*5.08*0.000885*523).

FAQ

What is Thrust for given liftoff distance?

Thrust for Given Liftoff Distance is a measure of the minimum thrust required for an aircraft to take off from a given distance, considering the aircraft's weight, free stream density, reference area, maximum lift coefficient, and liftoff distance, ensuring a safe and efficient departure and is represented as T = 1.44*(W^2)/([g]*ρ_∞*S*C_L,max*s_LO) or Aircraft Thrust = 1.44*(Weight^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?

Thrust for Given Liftoff Distance is a measure of the minimum thrust required for an aircraft to take off from a given distance, considering the aircraft's weight, free stream density, reference area, maximum lift coefficient, and liftoff distance, ensuring a safe and efficient departure is calculated using Aircraft Thrust = 1.44*(Weight^2)/([g]*Freestream Density*Reference Area*Maximum Lift Coefficient*Liftoff Distance). To calculate Thrust for given liftoff distance, you need Weight (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, 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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