Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
Vinay Mishra has created this Calculator and 200+ more calculators!
Shikha Maurya
Indian Institute of Technology (IIT), Bombay
Shikha Maurya has verified this Calculator and 100+ more calculators!

11 Other formulas that you can solve using the same Inputs

Air Resistance Force
Air Resistance=Air Constant*Velocity^2 GO
Archimedes Principle
Archimedes Principle=Density*Acceleration Due To Gravity*Velocity GO
Wavelength Of The Wave(Using Velocity)
Wavelength Of A Wave=Velocity*Time Period Of Progressive Wave GO
Time Period (Using Velocity )
Time Period Of Progressive Wave=Wavelength/Velocity GO
Stokes Force
Stokes Force=6*pi*Radius*Dynamic viscosity*Velocity GO
Angular Frequency (Using Velocity )
Angular Frequency=(2*pi*Velocity)/Wavelength GO
Centripetal Force
Centripetal Force=(Mass*(Velocity)^2)/Radius GO
Frequency Of Wavelength ( Using Velocity )
frequency=Velocity/Wavelength Of A Wave GO
Wave Number (Using Angular Frequency)
Wave Number=Angular Frequency/Velocity GO
Kinetic Energy
Kinetic Energy=(Mass*Velocity^2)/2 GO
Wavelength Of The Wave(Using Frequency)
Wavelength=Velocity/frequency GO

11 Other formulas that calculate the same Output

Drag in an accelerated flight
Drag Force=(Thrust of an aircraft*cos(Thrust angle))-(Mass*[g]*(sin(Flight path angle)))-(Mass*Acceleration) GO
Drag force on the plate in boundary layer flow
Drag Force=0.73*Width*viscosity of fluid*Fluid Velocity*sqrt(Reynolds Number) GO
Drag force in falling sphere resistance method
Drag Force=3*pi*viscosity of fluid*velocity of sphere*diameter of sphere GO
Forces acting on body along the flight path
Drag Force=(Weight*sin(Angle of Inclination))-(Mass*Velocity Gradient) GO
Drag for a level, unaccelerated flight
Drag Force=Thrust of an aircraft*(cos(Thrust angle)) GO
Drag for a level, unaccelerated flight at negligible thrust angle
Drag Force=Dynamic Pressure*Area*Drag Coefficient GO
Drag force
Drag Force=Drag Coefficient*Dynamic Pressure*Area GO
Total Drag for given excess power
Drag Force=Thrust force-(Excess Power/Velocity) GO
Drag force with angle of attack
Drag Force=Lift force/cot(Angle of attack) GO
Drag for given glide angle
Drag Force=Lift force*tan(Glide angle) GO
Total drag for given required power
Drag Force=Power/Freestream Velocity GO

Drag during ground effect Formula

Drag Force=(Parasite Drag coefficient+(((lift coefficient^2)*Ground effect factor)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)))*(0.5*Freestream density*(Velocity^2)*Reference Area)
F<sub>D</sub>=(C<sub>D,e</sub>+(((C<sub>L</sub>^2)*ϕ)/(pi*e*AR)))*(0.5*ρ<sub>∞</sub>*(v^2)*S)
More formulas
Resistance force during ground roll GO
Coefficient of rolling friction during ground roll GO
Weight of aircraft during ground roll GO
Lift acting on aircraft during ground roll GO
Ground effect factor GO
Liftoff velocity for given stall velocity GO
Stall velocity for given liftoff velocity GO
Liftoff velocity for given weight GO
Stall velocity for given weight GO
Maximum Lift coefficient for given stall velocity GO
Maximum Lift coefficient for given liftoff velocity GO
Liftoff distance GO
Thrust for given liftoff distance GO

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*(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 and is denoted by FD 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 (CD,e), lift coefficient (CL), Ground effect factor (ϕ), Oswald efficiency factor (e), Aspect Ratio of a wing (AR), Freestream density ), Velocity (v) and Reference Area (S) and hit the calculate button. Here is how the Drag during ground effect calculation can be explained with given input values -> 125312.3 = (5+(((10^2)*0.4)/(pi*0.5*4)))*(0.5*1.225*(60^2)*5).

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 FDD,e+(((CL^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*(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 (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. , 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, Velocity, in physics, is a vector quantity (it has both magnitude and direction), and is the time rate of change of position (of an object). and 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*(Velocity^2)*Reference Area). To calculate Drag during ground effect, you need Parasite Drag coefficient (CD,e), lift coefficient (CL), Ground effect factor (ϕ), Oswald efficiency factor (e), Aspect Ratio of a wing (AR), Freestream density ), Velocity (v) and 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, Velocity and Reference Area 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 Drag Force?
In this formula, Drag Force uses Parasite Drag coefficient, lift coefficient, Ground effect factor, Oswald efficiency factor, Aspect Ratio of a wing, Freestream density, Velocity and Reference Area. We can use 11 other way(s) to calculate the same, which is/are as follows -
  • Drag Force=Drag Coefficient*Dynamic Pressure*Area
  • Drag Force=(Weight*sin(Angle of Inclination))-(Mass*Velocity Gradient)
  • Drag Force=(Thrust of an aircraft*cos(Thrust angle))-(Mass*[g]*(sin(Flight path angle)))-(Mass*Acceleration)
  • Drag Force=Thrust of an aircraft*(cos(Thrust angle))
  • Drag Force=Dynamic Pressure*Area*Drag Coefficient
  • Drag Force=Lift force/cot(Angle of attack)
  • Drag Force=Power/Freestream Velocity
  • Drag Force=Thrust force-(Excess Power/Velocity)
  • Drag Force=Lift force*tan(Glide angle)
  • Drag Force=3*pi*viscosity of fluid*velocity of sphere*diameter of sphere
  • Drag Force=0.73*Width*viscosity of fluid*Fluid Velocity*sqrt(Reynolds Number)
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