Weight of aircraft during ground roll Calculator

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✖Rolling Resistance (or Rolling friction) is the force resisting the motion of a rolling body on a surface.ⓘ Rolling Resistance [R]			+10% -10%
✖Coefficient of Rolling Friction is the ratio of the force of rolling friction to the total weight of the object.ⓘ Coefficient of Rolling Friction [μ_r]			+10% -10%
✖The Lift Force, lifting force or simply lift is the sum of all the forces on a body that force it to move perpendicular to the direction of flow.ⓘ Lift Force [F_L]			+10% -10%

✖Weight Newton is a vector quantity and defined as the product of mass and acceleration acting on that mass.ⓘ Weight of aircraft during ground roll [W]

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Formula

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Weight of aircraft during ground roll

Formula

`"W" = ("R"/"μ"_{"r"})+"F"_{"L"}`

Example

`"60.5N"=("5N"/"0.1")+"10.5N"`

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Weight of aircraft during ground roll Solution

STEP 0: Pre-Calculation Summary

Formula Used

Weight Newton = (Rolling Resistance/Coefficient of Rolling Friction)+Lift Force
W = (R/μ_r)+F_L
This formula uses 4 Variables

Variables Used

Weight Newton - (Measured in Newton) - Weight Newton is a vector quantity and defined as the product of mass and acceleration acting on that mass.
Rolling Resistance - (Measured in Newton) - Rolling Resistance (or Rolling friction) is the force resisting the motion of a rolling body on a surface.
Coefficient of Rolling Friction - Coefficient of Rolling Friction is the ratio of the force of rolling friction to the total weight of the object.
Lift Force - (Measured in Newton) - The Lift Force, lifting force or simply lift is the sum of all the forces on a body that force it to move perpendicular to the direction of flow.

STEP 1: Convert Input(s) to Base Unit

Rolling Resistance: 5 Newton --> 5 Newton No Conversion Required
Coefficient of Rolling Friction: 0.1 --> No Conversion Required
Lift Force: 10.5 Newton --> 10.5 Newton No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

W = (R/μ_r)+F_L --> (5/0.1)+10.5

Evaluating ... ...

W = 60.5

STEP 3: Convert Result to Output's Unit

60.5 Newton --> No Conversion Required

FINAL ANSWER

60.5 Newton <-- Weight Newton

(Calculation completed in 00.004 seconds)

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Home » Physics » Aircraft Mechanics » Aircraft Performance » Take-off and Landing » Take-Off » Weight of aircraft during ground roll

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

Weight of aircraft during ground roll Formula

Weight Newton = (Rolling Resistance/Coefficient of Rolling Friction)+Lift Force
W = (R/μ_r)+F_L

How do planes steer on the ground?

Steering on the ground is achieved by turning the nose wheel, either by a tiller wheel in the cockpit or by using the rudder pedals.

How to Calculate Weight of aircraft during ground roll?

Weight of aircraft during ground roll calculator uses Weight Newton = (Rolling Resistance/Coefficient of Rolling Friction)+Lift Force to calculate the Weight Newton, The Weight of aircraft during ground roll refers to the total mass of the aircraft, including its fuel, passengers, cargo, and any other payload, as it moves along the ground before takeoff or after landing. Weight Newton is denoted by W symbol.

How to calculate Weight of aircraft during ground roll using this online calculator? To use this online calculator for Weight of aircraft during ground roll, enter Rolling Resistance (R), Coefficient of Rolling Friction (μ_r) & Lift Force (F_L) and hit the calculate button. Here is how the Weight of aircraft during ground roll calculation can be explained with given input values -> 60.5 = (5/0.1)+10.5.

FAQ

What is Weight of aircraft during ground roll?

The Weight of aircraft during ground roll refers to the total mass of the aircraft, including its fuel, passengers, cargo, and any other payload, as it moves along the ground before takeoff or after landing and is represented as W = (R/μ_r)+F_L or Weight Newton = (Rolling Resistance/Coefficient of Rolling Friction)+Lift Force. Rolling Resistance (or Rolling friction) is the force resisting the motion of a rolling body on a surface, Coefficient of Rolling Friction is the ratio of the force of rolling friction to the total weight of the object & The Lift Force, lifting force or simply lift is the sum of all the forces on a body that force it to move perpendicular to the direction of flow.

How to calculate Weight of aircraft during ground roll?

The Weight of aircraft during ground roll refers to the total mass of the aircraft, including its fuel, passengers, cargo, and any other payload, as it moves along the ground before takeoff or after landing is calculated using Weight Newton = (Rolling Resistance/Coefficient of Rolling Friction)+Lift Force. To calculate Weight of aircraft during ground roll, you need Rolling Resistance (R), Coefficient of Rolling Friction (μ_r) & Lift Force (F_L). With our tool, you need to enter the respective value for Rolling Resistance, Coefficient of Rolling Friction & 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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