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Landing ground roll distance using thrust reversal Calculator

Category Physics ↺
Physics Flight Stability and Control ↺
Flight-Stability-And-Control Airplane Performance ↺
Airplane-Performance Landing Performance ↺
✖Weight is a vector quantity and defined as the product of mass and acceleration acting on that massⓘ Weight [W]
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✖Freestream density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitudeⓘ Freestream density [ρ∞]
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✖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]
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✖Maximum Lift Coefficient is defined as the lift coefficient of the airfoil at stalling angle of attackⓘ Maximum Lift Coefficient [CL,max]
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✖Touchdown Velocity is the instantaneous velocity of an aircraft when it touches the ground during landingⓘ Touchdown Velocity [VT]
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✖The Zero-lift drag coefficient is a dimensionless parameter that relates an aircraft's zero-lift drag force to its size, speed, and flying altitudeⓘ Zero-lift drag coefficient [CD,0]
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✖Ground effect factor is the ratio of the induced drag in-ground-effect to the induced drag out-of-ground-effectⓘ Ground effect factor [ϕ]
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✖The lift coefficient (CL) is a dimensionless coefficient that relates the lift generated by a lifting body to the fluid density around the body, the fluid velocity and an associated reference area. ⓘ lift coefficient [CL]
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✖The Oswald efficiency factor is a correction factor that represents the change in drag with lift of a three-dimensional wing or airplane, as compared with an ideal wing having the same aspect ratioⓘ Oswald efficiency factor [e]
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✖The Aspect Ratio of a wing is defined as the ratio of its span to its mean chord.ⓘ Aspect Ratio of a wing [AR]
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✖Reverse thrust is the temporary diversion of an aircraft engine's thrust for it to act against the forward travel of the aircraft, providing decelerationⓘ Reverse thrust [Treverse]
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✖Coefficient of Rolling Friction is the ratio of the force of rolling friction to the total weight of the objectⓘ Coefficient of Rolling Friction [μr]
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✖The Landing Roll distance is the distance covered when the aircraft touches down, is brought down to taxi speed, and eventually comes to a complete stopⓘ Landing ground roll distance using thrust reversal [sL]
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Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
Vinay Mishra has created this Calculator and 300+ more calculators!
Sanjay Krishna
Amrita School of Engineering (ASE), Vallikavu
Sanjay Krishna has verified this Calculator and 200+ more calculators!

11 Other formulas that you can solve using the same Inputs

Drag Coefficient for given zero-lift drag coefficient
Drag Coefficient=Zero-lift drag coefficient+((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)) GO
Drag Coefficient for given parasite drag coefficient
Drag Coefficient=Parasite Drag coefficient+((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)) GO
Coefficient of Drag due to lift
Coefficient of drag due to lift=(lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing) 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
Thrust-to-weight ratio
Thrust-to-weight ratio=Drag Coefficient/lift coefficient GO
Dynamic pressure based on coefficient of lift
Dynamic Pressure=Lift force/(lift coefficient*Area) GO
Lift for a level, unaccelerated flight at negligible thrust angle
Lift force=Dynamic Pressure*Area*lift coefficient GO
Lift Force
Lift force=lift coefficient*Dynamic Pressure*Area GO
Weight of aircraft for a level, unaccelerated flight at negligible thrust angle
Weight=Dynamic Pressure*Area*lift coefficient GO

1 Other formulas that calculate the same Output

Landing ground roll distance
Landing Roll=1.69*(Weight^2)*(1/([g]*Freestream density*Reference Area*Maximum Lift Coefficient))*(1/((0.5*Freestream density*((0.7*Touchdown Velocity)^2)*Reference Area*(Zero-lift drag coefficient+(Ground effect factor*(lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing))))+(Coefficient of Rolling Friction*(Weight-(0.5*Freestream density*((0.7*Touchdown Velocity)^2)*Reference Area*lift coefficient))))) GO

Landing ground roll distance using thrust reversal Formula

Landing Roll=1.69*(Weight^2)*(1/([g]*Freestream density*Reference Area*Maximum Lift Coefficient))*(1/((0.5*Freestream density*((0.7*Touchdown Velocity)^2)*Reference Area*(Zero-lift drag coefficient+(Ground effect factor*(lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing))))+(Reverse thrust)+(Coefficient of Rolling Friction*(Weight-(0.5*Freestream density*((0.7*Touchdown Velocity)^2)*Reference Area*lift coefficient)))))
s<sub>L</sub>=1.69*(W^2)*(1/([g]*ρ<sub>∞</sub>*S*C<sub>L,max</sub>))*(1/((0.5*ρ<sub>∞</sub>*((0.7*V<sub>T</sub>)^2)*S*(C<sub>D,0</sub>+(ϕ*(C<sub>L</sub>^2)/(pi*e*AR))))+(T<sub>reverse</sub>)+(μ<sub>r</sub>*(W-(0.5*ρ<sub>∞</sub>*((0.7*V<sub>T</sub>)^2)*S*C<sub>L</sub>)))))
More formulas
Touchdown velocity GO
Touchdown velocity for given stall velocity GO
Stall velocity for given touchdown velocity GO
Landing ground roll distance GO

Why is landing dangerous?

49% of all fatal accidents happen during the final descent and landing phases of the average flight, while 14% of all fatal accidents occur during takeoff and initial climb. During takeoff and landing, pilots have less time to react to problems because they're on or close to the ground and moving quickly.

How to Calculate Landing ground roll distance using thrust reversal?

Landing ground roll distance using thrust reversal calculator uses Landing Roll=1.69*(Weight^2)*(1/([g]*Freestream density*Reference Area*Maximum Lift Coefficient))*(1/((0.5*Freestream density*((0.7*Touchdown Velocity)^2)*Reference Area*(Zero-lift drag coefficient+(Ground effect factor*(lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing))))+(Reverse thrust)+(Coefficient of Rolling Friction*(Weight-(0.5*Freestream density*((0.7*Touchdown Velocity)^2)*Reference Area*lift coefficient))))) to calculate the Landing Roll, Landing ground roll distance using thrust reversal is a function of weight, reversed thrust, freestream density, maximum lift coefficient, touchdown velocity, coefficient of rolling friction (between the tires and ground), ground effect factor, lift and drag of the aircraft. Landing Roll and is denoted by sL symbol.

How to calculate Landing ground roll distance using thrust reversal using this online calculator? To use this online calculator for Landing ground roll distance using thrust reversal, enter Weight (W), Freestream density (ρ∞), Reference Area (S), Maximum Lift Coefficient (CL,max), Touchdown Velocity (VT), Zero-lift drag coefficient (CD,0), Ground effect factor (ϕ), lift coefficient (CL), Oswald efficiency factor (e), Aspect Ratio of a wing (AR), Reverse thrust (Treverse) and Coefficient of Rolling Friction (μr) and hit the calculate button. Here is how the Landing ground roll distance using thrust reversal calculation can be explained with given input values -> 0.000566 = 1.69*(100^2)*(1/([g]*1.225*5*1.65))*(1/((0.5*1.225*((0.7*193)^2)*5*(0.0161+(0.4*(10^2)/(pi*0.5*4))))+(550)+(0.1*(100-(0.5*1.225*((0.7*193)^2)*5*10))))).

FAQ

What is Landing ground roll distance using thrust reversal?
Landing ground roll distance using thrust reversal is a function of weight, reversed thrust, freestream density, maximum lift coefficient, touchdown velocity, coefficient of rolling friction (between the tires and ground), ground effect factor, lift and drag of the aircraft and is represented as sL=1.69*(W^2)*(1/([g]*ρ∞*S*CL,max))*(1/((0.5*ρ∞*((0.7*VT)^2)*S*(CD,0+(ϕ*(CL^2)/(pi*e*AR))))+(Treverse)+(μr*(W-(0.5*ρ∞*((0.7*VT)^2)*S*CL))))) or Landing Roll=1.69*(Weight^2)*(1/([g]*Freestream density*Reference Area*Maximum Lift Coefficient))*(1/((0.5*Freestream density*((0.7*Touchdown Velocity)^2)*Reference Area*(Zero-lift drag coefficient+(Ground effect factor*(lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing))))+(Reverse thrust)+(Coefficient of Rolling Friction*(Weight-(0.5*Freestream density*((0.7*Touchdown Velocity)^2)*Reference Area*lift coefficient))))). 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, Touchdown Velocity is the instantaneous velocity of an aircraft when it touches the ground during landing, The Zero-lift drag coefficient is a dimensionless parameter that relates an aircraft's zero-lift drag force to its size, speed, and flying altitude, Ground effect factor is the ratio of the induced drag in-ground-effect to the induced drag out-of-ground-effect, The lift coefficient (CL) is a dimensionless coefficient that relates the lift generated by a lifting body to the fluid density around the body, the fluid velocity and an associated reference area. , The Oswald efficiency factor is a correction factor that represents the change in drag with lift of a three-dimensional wing or airplane, as compared with an ideal wing having the same aspect ratio, The Aspect Ratio of a wing is defined as the ratio of its span to its mean chord, Reverse thrust is the temporary diversion of an aircraft engine's thrust for it to act against the forward travel of the aircraft, providing deceleration and Coefficient of Rolling Friction is the ratio of the force of rolling friction to the total weight of the object.
How to calculate Landing ground roll distance using thrust reversal?
Landing ground roll distance using thrust reversal is a function of weight, reversed thrust, freestream density, maximum lift coefficient, touchdown velocity, coefficient of rolling friction (between the tires and ground), ground effect factor, lift and drag of the aircraft is calculated using Landing Roll=1.69*(Weight^2)*(1/([g]*Freestream density*Reference Area*Maximum Lift Coefficient))*(1/((0.5*Freestream density*((0.7*Touchdown Velocity)^2)*Reference Area*(Zero-lift drag coefficient+(Ground effect factor*(lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing))))+(Reverse thrust)+(Coefficient of Rolling Friction*(Weight-(0.5*Freestream density*((0.7*Touchdown Velocity)^2)*Reference Area*lift coefficient))))). To calculate Landing ground roll distance using thrust reversal, you need Weight (W), Freestream density (ρ∞), Reference Area (S), Maximum Lift Coefficient (CL,max), Touchdown Velocity (VT), Zero-lift drag coefficient (CD,0), Ground effect factor (ϕ), lift coefficient (CL), Oswald efficiency factor (e), Aspect Ratio of a wing (AR), Reverse thrust (Treverse) and Coefficient of Rolling Friction (μr). With our tool, you need to enter the respective value for Weight, Freestream density, Reference Area, Maximum Lift Coefficient, Touchdown Velocity, Zero-lift drag coefficient, Ground effect factor, lift coefficient, Oswald efficiency factor, Aspect Ratio of a wing, Reverse thrust and Coefficient of Rolling Friction and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.
How many ways are there to calculate Landing Roll?
In this formula, Landing Roll uses Weight, Freestream density, Reference Area, Maximum Lift Coefficient, Touchdown Velocity, Zero-lift drag coefficient, Ground effect factor, lift coefficient, Oswald efficiency factor, Aspect Ratio of a wing, Reverse thrust and Coefficient of Rolling Friction. We can use 1 other way(s) to calculate the same, which is/are as follows -
  • Landing Roll=1.69*(Weight^2)*(1/([g]*Freestream density*Reference Area*Maximum Lift Coefficient))*(1/((0.5*Freestream density*((0.7*Touchdown Velocity)^2)*Reference Area*(Zero-lift drag coefficient+(Ground effect factor*(lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing))))+(Coefficient of Rolling Friction*(Weight-(0.5*Freestream density*((0.7*Touchdown Velocity)^2)*Reference Area*lift coefficient)))))
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