Drag during ground effect Calculator

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Introduction and Governing Equations

Static Stability and Control

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✖The parasite Drag coefficient is defined as the combination of coefficients of form drag and skin friction drag.ⓘ Parasite Drag coefficient [C_D,e]			+10% -10%
✖The Lift Coefficient 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 [C_L]			+10% -10%
✖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]			+10% -10%
✖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]			+10% -10%
✖The Aspect Ratio of a wing is defined as the ratio of its span to its mean chord.ⓘ Aspect Ratio of a wing [AR]			+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%
✖Flight Velocity is the speed with which the aircraft moves through air.ⓘ Flight Velocity [V]			+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%

✖Drag Force is the resisting force experienced by an object moving through a fluid.ⓘ Drag during ground effect [F_D]

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Formula

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Drag during ground effect

Formula

`"F"_{"D"} = ("C"_{"D,e"}+((("C"_{"L"}^2)*"ϕ")/(pi*"e"*"AR")))*(0.5*"ρ"_{"∞"}*("V"^2)*"S")`

Example

`"71977.67N"=("4.5"+(((("5.5")^2)*"0.4")/(pi*"0.5"*"4")))*(0.5*"1.225kg/m³"*(("60m/s")^2)*"5.08m²")`

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Drag during ground effect Solution

STEP 0: Pre-Calculation Summary

Formula Used

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)
F_D = (C_D,e+(((C_L^2)*ϕ)/(pi*e*AR)))*(0.5*ρ_∞*(V^2)*S)
This formula uses 1 Constants, 9 Variables

Constants Used

pi - Archimedes' constant Value Taken As 3.14159265358979323846264338327950288

Variables Used

Drag Force - (Measured in Newton) - Drag Force is the resisting force experienced by an object moving through a fluid.
Parasite Drag coefficient - The parasite Drag coefficient is defined as the combination of coefficients of form drag and skin friction drag.
Lift Coefficient - The Lift Coefficient 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.
Ground effect factor - Ground effect factor is the ratio of the induced drag in-ground-effect to the induced drag out-of-ground-effect.
Oswald efficiency factor - 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.
Aspect Ratio of a wing - The Aspect Ratio of a wing is defined as the ratio of its span to its mean chord.
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.
Flight Velocity - (Measured in Meter per Second) - Flight Velocity is the speed with which the aircraft moves through air.
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.

STEP 1: Convert Input(s) to Base Unit

Parasite Drag coefficient: 4.5 --> No Conversion Required
Lift Coefficient: 5.5 --> No Conversion Required
Ground effect factor: 0.4 --> No Conversion Required
Oswald efficiency factor: 0.5 --> No Conversion Required
Aspect Ratio of a wing: 4 --> No Conversion Required
Freestream density: 1.225 Kilogram per Cubic Meter --> 1.225 Kilogram per Cubic Meter No Conversion Required
Flight Velocity: 60 Meter per Second --> 60 Meter per Second No Conversion Required
Reference Area: 5.08 Square Meter --> 5.08 Square Meter No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

F_D = (C_D,e+(((C_L^2)*ϕ)/(pi*e*AR)))*(0.5*ρ_∞*(V^2)*S) --> (4.5+(((5.5^2)*0.4)/(pi*0.5*4)))*(0.5*1.225*(60^2)*5.08)

Evaluating ... ...

F_D = 71977.6739725496

STEP 3: Convert Result to Output's Unit

71977.6739725496 Newton --> No Conversion Required

FINAL ANSWER

71977.6739725496 ≈ 71977.67 Newton <-- Drag Force

(Calculation completed in 00.004 seconds)

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Home » Physics » Aircraft Mechanics » Aircraft Performance » Take-off and Landing » Take-Off » Drag during ground effect

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

Drag during ground effect Formula

What does ground effect mean?

Ground effect is the apparent increase in aerodynamic lift experienced by an aircraft when flying near the ground and observed up to a distance above the ground approximately equal to the wingspan.

How to Calculate Drag during ground effect?

Drag during ground effect calculator uses 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) to calculate the Drag Force, The Drag during ground effect is the aerodynamic drag that an aircraft's wings generate during takeoff and is a function of the ground effect factor. Drag Force is denoted by F_D symbol.

How to calculate Drag during ground effect using this online calculator? To use this online calculator for Drag during ground effect, enter Parasite Drag coefficient (C_D,e), Lift Coefficient (C_L), Ground effect factor (ϕ), Oswald efficiency factor (e), Aspect Ratio of a wing (AR), Freestream density (ρ_∞), Flight Velocity (V) & Reference Area (S) and hit the calculate button. Here is how the Drag during ground effect calculation can be explained with given input values -> 71977.67 = (4.5+(((5.5^2)*0.4)/(pi*0.5*4)))*(0.5*1.225*(60^2)*5.08).

FAQ

What is Drag during ground effect?

The Drag during ground effect is the aerodynamic drag that an aircraft's wings generate during takeoff and is a function of the ground effect factor and is represented as F_D = (C_D,e+(((C_L^2)*ϕ)/(pi*e*AR)))*(0.5*ρ_∞*(V^2)*S) or 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). The parasite Drag coefficient is defined as the combination of coefficients of form drag and skin friction drag, The Lift Coefficient 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, Ground effect factor is the ratio of the induced drag in-ground-effect to the induced drag out-of-ground-effect, 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, Freestream density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude, Flight Velocity is the speed with which the aircraft moves through air & 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.

How to calculate Drag during ground effect?

The Drag during ground effect is the aerodynamic drag that an aircraft's wings generate during takeoff and is a function of the ground effect factor is calculated using 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). To calculate Drag during ground effect, you need Parasite Drag coefficient (C_D,e), Lift Coefficient (C_L), Ground effect factor (ϕ), Oswald efficiency factor (e), Aspect Ratio of a wing (AR), Freestream density (ρ_∞), Flight Velocity (V) & Reference Area (S). With our tool, you need to enter the respective value for Parasite Drag coefficient, Lift Coefficient, Ground effect factor, Oswald efficiency factor, Aspect Ratio of a wing, Freestream density, Flight Velocity & Reference Area 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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