Landing Ground Run Calculator

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Aircraft Performance

Aircraft Design

Introduction and Governing Equations

Static Stability and Control

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✖the normal force acting on the aircraft during the landing roll (which is equal to the aircraft's weight divided by the gravitational acceleration).ⓘ Normal Force [N]			+10% -10%
✖Velocity at Touchdown Point represents the touchdown speed of the aircraft.ⓘ Velocity at Touchdown Point [V_TD]			+10% -10%
✖Weight Of Aircraft is a force which is always directed towards the center of the earth.ⓘ Weight Of Aircraft [W]			+10% -10%
✖Velocity of Aircraft is the velocity, or airspeed, at which a plane flies.ⓘ Velocity of Aircraft [V_∞]			+10% -10%
✖Reverse thrust is a mechanism used by jet engines, particularly on aircraft, to help slow down the aircraft after landing.ⓘ Reverse Thrust [V_TR]			+10% -10%
✖Drag force, also known as air resistance, is the aerodynamic force that opposes the motion of an aircraft through the air.ⓘ Drag Force [D]			+10% -10%
✖The Reference Of Rolling Resistance Coefficient is the ratio of the rolling resistance force to the wheel load. It's a basic resistance when moving objects.ⓘ Reference Of Rolling Resistance Coefficient [μ_r]			+10% -10%
✖Lift Force is the upward force that holds an aircraft in the air, generated by the interaction of the aircraft with a fluid, such as air.ⓘ Lift Force [L]			+10% -10%

✖Landing Ground Run typically refers to the distance a aircraft requires to come to a complete stop after landing on a runway.ⓘ Landing Ground Run [Sg_l]

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Formula

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Landing Ground Run

Formula

`"Sg"_{"l"} = ("N"*"V"_{"TD"})+("W"/(2*"[g]"))*int((2*"V"_{"∞"})/("V"_{"TR"}+"D"+"μ"_{"r"}*("W"-"L")),x,0,"V"_{"TD"})`

Example

`"17412.9m"=("3N"*"23m/s")+("2000kg"/(2*"[g]"))*int((2*"292m/s")/("6N"+"65N"+"0.004"*("2000kg"-"7N")),x,0,"23m/s")`

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Landing Ground Run Solution

STEP 0: Pre-Calculation Summary

Formula Used

Landing Ground Run = (Normal Force*Velocity at Touchdown Point)+(Weight Of Aircraft/(2*[g]))*int((2*Velocity of Aircraft)/(Reverse Thrust+Drag Force+Reference Of Rolling Resistance Coefficient*(Weight Of Aircraft-Lift Force)),x,0,Velocity at Touchdown Point)
Sg_l = (N*V_TD)+(W/(2*[g]))*int((2*V_∞)/(V_TR+D+μ_r*(W-L)),x,0,V_TD)
This formula uses 1 Constants, 1 Functions, 9 Variables

Constants Used

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

Functions Used

int - The definite integral can be used to calculate net signed area, which is the area above the x -axis minus the area below the x -axis., int(expr, arg, from, to)

Variables Used

Landing Ground Run - (Measured in Meter) - Landing Ground Run typically refers to the distance a aircraft requires to come to a complete stop after landing on a runway.
Normal Force - (Measured in Newton) - the normal force acting on the aircraft during the landing roll (which is equal to the aircraft's weight divided by the gravitational acceleration).
Velocity at Touchdown Point - (Measured in Meter per Second) - Velocity at Touchdown Point represents the touchdown speed of the aircraft.
Weight Of Aircraft - (Measured in Kilogram) - Weight Of Aircraft is a force which is always directed towards the center of the earth.
Velocity of Aircraft - (Measured in Meter per Second) - Velocity of Aircraft is the velocity, or airspeed, at which a plane flies.
Reverse Thrust - (Measured in Newton) - Reverse thrust is a mechanism used by jet engines, particularly on aircraft, to help slow down the aircraft after landing.
Drag Force - (Measured in Newton) - Drag force, also known as air resistance, is the aerodynamic force that opposes the motion of an aircraft through the air.
Reference Of Rolling Resistance Coefficient - The Reference Of Rolling Resistance Coefficient is the ratio of the rolling resistance force to the wheel load. It's a basic resistance when moving objects.
Lift Force - (Measured in Newton) - Lift Force is the upward force that holds an aircraft in the air, generated by the interaction of the aircraft with a fluid, such as air.

STEP 1: Convert Input(s) to Base Unit

Normal Force: 3 Newton --> 3 Newton No Conversion Required
Velocity at Touchdown Point: 23 Meter per Second --> 23 Meter per Second No Conversion Required
Weight Of Aircraft: 2000 Kilogram --> 2000 Kilogram No Conversion Required
Velocity of Aircraft: 292 Meter per Second --> 292 Meter per Second No Conversion Required
Reverse Thrust: 6 Newton --> 6 Newton No Conversion Required
Drag Force: 65 Newton --> 65 Newton No Conversion Required
Reference Of Rolling Resistance Coefficient: 0.004 --> No Conversion Required
Lift Force: 7 Newton --> 7 Newton No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

Sg_l = (N*V_TD)+(W/(2*[g]))*int((2*V_∞)/(V_TR+D+μ_r*(W-L)),x,0,V_TD) --> (3*23)+(2000/(2*[g]))*int((2*292)/(6+65+0.004*(2000-7)),x,0,23)

Evaluating ... ...

Sg_l = 17412.9043872759

STEP 3: Convert Result to Output's Unit

17412.9043872759 Meter --> No Conversion Required

FINAL ANSWER

17412.9043872759 ≈ 17412.9 Meter <-- Landing Ground Run

(Calculation completed in 00.004 seconds)

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Sri Ramakrishna Engineering College (SREC), COIMBATORE

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< 5 Landing Calculators

Landing ground roll distance

Go Landing Roll = 1.69*(Weight Newton^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 Newton-(0.5*Freestream density*((0.7*Touchdown Velocity)^2)*Reference Area*Lift Coefficient)))))

Landing Ground Run

Go Landing Ground Run = (Normal Force*Velocity at Touchdown Point)+(Weight Of Aircraft/(2*[g]))*int((2*Velocity of Aircraft)/(Reverse Thrust+Drag Force+Reference Of Rolling Resistance Coefficient*(Weight Of Aircraft-Lift Force)),x,0,Velocity at Touchdown Point)

Touchdown velocity

Go Touchdown Velocity = 1.3*(sqrt(2*Weight Newton/(Freestream density*Reference Area*Maximum Lift Coefficient)))

Touchdown velocity for given stall velocity

Go Touchdown Velocity = 1.3*Stall Velocity

Stall velocity for given touchdown velocity

Go Stall Velocity = Touchdown Velocity/1.3

Landing Ground Run Formula

What is Landing Ground Run

The landing ground run, also known as landing roll or landing distance, refers to the distance an aircraft requires to land and come to a complete stop on the runway after touchdown. It includes the distance covered during the touchdown, rollout, and deceleration phases of the landing.

How to Calculate Landing Ground Run?

Landing Ground Run calculator uses Landing Ground Run = (Normal Force*Velocity at Touchdown Point)+(Weight Of Aircraft/(2*[g]))*int((2*Velocity of Aircraft)/(Reverse Thrust+Drag Force+Reference Of Rolling Resistance Coefficient*(Weight Of Aircraft-Lift Force)),x,0,Velocity at Touchdown Point) to calculate the Landing Ground Run, The Landing Ground Run formula calculates the distance required for an aircraft to come to a complete stop after landing. This formula incorporates various factors such as aircraft characteristics, landing conditions, and pilot technique. Landing Ground Run is denoted by Sg_l symbol.

How to calculate Landing Ground Run using this online calculator? To use this online calculator for Landing Ground Run, enter Normal Force (N), Velocity at Touchdown Point (V_TD), Weight Of Aircraft (W), Velocity of Aircraft (V_∞), Reverse Thrust (V_TR), Drag Force (D), Reference Of Rolling Resistance Coefficient (μ_r) & Lift Force (L) and hit the calculate button. Here is how the Landing Ground Run calculation can be explained with given input values -> 174129 = (3*23)+(2000/(2*[g]))*int((2*292)/(6+65+0.004*(2000-7)),x,0,23).

FAQ

What is Landing Ground Run?

The Landing Ground Run formula calculates the distance required for an aircraft to come to a complete stop after landing. This formula incorporates various factors such as aircraft characteristics, landing conditions, and pilot technique and is represented as Sg_l = (N*V_TD)+(W/(2*[g]))*int((2*V_∞)/(V_TR+D+μ_r*(W-L)),x,0,V_TD) or Landing Ground Run = (Normal Force*Velocity at Touchdown Point)+(Weight Of Aircraft/(2*[g]))*int((2*Velocity of Aircraft)/(Reverse Thrust+Drag Force+Reference Of Rolling Resistance Coefficient*(Weight Of Aircraft-Lift Force)),x,0,Velocity at Touchdown Point). the normal force acting on the aircraft during the landing roll (which is equal to the aircraft's weight divided by the gravitational acceleration), Velocity at Touchdown Point represents the touchdown speed of the aircraft, Weight Of Aircraft is a force which is always directed towards the center of the earth, Velocity of Aircraft is the velocity, or airspeed, at which a plane flies, Reverse thrust is a mechanism used by jet engines, particularly on aircraft, to help slow down the aircraft after landing, Drag force, also known as air resistance, is the aerodynamic force that opposes the motion of an aircraft through the air, The Reference Of Rolling Resistance Coefficient is the ratio of the rolling resistance force to the wheel load. It's a basic resistance when moving objects & Lift Force is the upward force that holds an aircraft in the air, generated by the interaction of the aircraft with a fluid, such as air.

How to calculate Landing Ground Run?

The Landing Ground Run formula calculates the distance required for an aircraft to come to a complete stop after landing. This formula incorporates various factors such as aircraft characteristics, landing conditions, and pilot technique is calculated using Landing Ground Run = (Normal Force*Velocity at Touchdown Point)+(Weight Of Aircraft/(2*[g]))*int((2*Velocity of Aircraft)/(Reverse Thrust+Drag Force+Reference Of Rolling Resistance Coefficient*(Weight Of Aircraft-Lift Force)),x,0,Velocity at Touchdown Point). To calculate Landing Ground Run, you need Normal Force (N), Velocity at Touchdown Point (V_TD), Weight Of Aircraft (W), Velocity of Aircraft (V_∞), Reverse Thrust (V_TR), Drag Force (D), Reference Of Rolling Resistance Coefficient (μ_r) & Lift Force (L). With our tool, you need to enter the respective value for Normal Force, Velocity at Touchdown Point, Weight Of Aircraft, Velocity of Aircraft, Reverse Thrust, Drag Force, Reference Of Rolling Resistance Coefficient & Lift Force 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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