# Ground effect on the aerodynamics of a naca 0015 airfoil with a plain trailing-edge flap

@inproceedings{Dionne2018GroundEO,
title={Ground effect on the aerodynamics of a naca 0015 airfoil with a plain trailing-edge flap},
author={V Tremblay Dionne and T. Lee},
year={2018}
}
• Published 25 January 2018
• Engineering
Submit Manuscript | http://medcraveonline.com Abbreviations: c: chord; u∞ : Free Stream Velocity; ν: Kinematic Viscosity; Re: Chord Reynolds number, ( ) / u c n ∞ = ; OGE: Out of the Ground Effect; GE: Ground Effect; Cd: Sectional Drag Coefficient; Cdp: Sectional Pressure Drag Coefficient; Cl: Sectional Lift Coefficient; Cl,max: Maximum Cl; l C α :Lift-Curve Slope; Cm: Sectional Pitching Moment Coefficient; Cm,peak: Peak Cm Value; p∞ : Freestream Pressure; Cp : Surface Pressure Coefficient, 2…
4 Citations

## Figures and Tables from this paper

Effect of Trailing-Edge Flap Deflection on a Symmetric Airfoil Over a Wavy Ground
• Engineering
Journal of Fluids Engineering
• 2018
The effect of trailing-edge flap (TEF) deflection on the aerodynamic properties and flowfield of a symmetric airfoil over a wavy ground was investigated experimentally. This Technical Brief is a
The ground effect on flapping Bio and NACA 0015 airfoils in power extraction and propulsion regimes
• Engineering, Physics
• 2020
In this study, the heaving and pitching motions of a biologically inspired airfoil (Bio airfoil) and a NACA 0015 airfoil in power extraction ( $${\text{Po}}$$ Po ) and propulsion ( $${\text{Pr}}$$ Pr
Experimental Study of Aerodynamics and Wingtip Vortex of a Rectangular Wing in Flat Ground Effect
• Physics, Engineering
Journal of Fluids Engineering
• 2019
The ground effect on the aerodynamics and tip vortex flow of a rectangular wing is investigated experimentally at Re = 2.71 × 105. The results show that there is a large lift increase with reducing
2D and 3D Potential Flow Simulations around NACA 0012 with Ground Effect
• Physics, Engineering
• 2021
The purpose of this paper is to develop a Boundary Element Based Method (BEM) for determining the steady potential about two and three dimensional airfoil. The numerical investigation of NACA 0012

## References

SHOWING 1-10 OF 17 REFERENCES
Aerodynamics of a NACA4412 Airfoil in Ground Effect
• Engineering, Physics
• 2007
The flow characteristics over a NACA4412 airfoil are studied in a low turbulence wind tunnel with moving ground simulation at a Reynolds number of 3.0 x 105 by varying the angle of attack from 0 to
Aerodynamics of a single element wing in ground effect
• Engineering, Physics
• 2000
An investigation was conducted on the performance characteristics and flowfield phenomena of a wing in ground effect. Model tests were performed in low-speed wind tunnels equipped with moving ground.
Impact of ground proximity on the aerodynamic properties of an unsteady airfoil
• Engineering, Physics
• 2018
The aerodynamic properties of a NACA 0012 airfoil, both stationary and unsteady, in ground effect (for nondimensional ground clearance h/c ≤ 60%) were investigated experimentally at Re = 98,000. For
Aerodynamics of a double element wing in ground effect
• Engineering
• 2000
An investigation of a cambered, double-element, high-lift wing operating in ground effect was performed. The effect of ground proximity and flap setting was quantified in terms of aerodynamic
Pitch Stability Analysis of an Airfoil in Ground Effect
• Engineering, Physics
• 2009
The effects of placing a slot through a two-dimensional Wortmann FX 63-137 airfoil in ground effect were examined using computational fluid dynamics. The geometric shape of the slot was varied in
Aerodynamic characteristics of a two-dimensional airfoil with ground effect
• Physics, Engineering
• 1996
The effect of Reynolds number on the aerodynamic characteristics of an airfoil with ground effect in viscous flow is investigated by numerical method. A numerical scheme, based on the standard k-e
An investigation into wing in ground effect aerofoil geometry
• Engineering
• 2002
Summary This paper details experimental results from wind tunnel studies of a DHMTU 12-35.3-10.2- 80.12 and NACA 0012 section operating in ground effect. It was found that the drag of the DHMTU