Abstract
The flow behind perforated Gurney-type flaps was investigated by using particle image velocimetry (PIV) at Re = 5.3 × 104. The PIV measurements were supplemented by force balance and surface pressure data. The near wake was disrupted and narrowed, indicative of a reduced drag, with increasing flap perforation and had a drastically suppressed fluctuating intensity. Depending on the strength of the perforation-generated jet, the vortex shedding process behind the flap could be eliminated. The flap porosity also led to reduced positive camber effects and the decompression of the cavity flow (upstream of the flap), as well as decreased upper and lower surface pressures, compared to the solid flap. The reduction in the drag, however, outweighed the loss in lift and rendered an improved lift-to-drag ratio.
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Abbreviations
- b :
-
span
- c :
-
airfoil chord
- C d :
-
section drag coefficient
- C d,min :
-
C d value at α = 0°
- C l :
-
section lift coefficient
- C p :
-
surface pressure coefficient
- d :
-
hole diameter
- f s :
-
vortex-shedding frequency
- h :
-
flap height
- Re :
-
Reynolds number (cu o/ν)
- St :
-
Strouhal number (f s h/u o)
- u o :
-
freestream velocity
- u m ,v m :
-
mean streamwise and transverse velocity
- u,v :
-
instantaneous streamwise and transverse velocity
- u′:
-
streamwise fluctuating velocity (u − u m )
- u rms, v rms :
-
root-mean-square turbulence intensity
- x,y,z :
-
streamwise, transverse and spanwise distance
- α:
-
angle of attack
- αss :
-
lift stall angle
- αzl :
-
zero-lift angle
- σ:
-
porosity
- ζ:
-
vorticity (∂v/∂x − ∂u/∂y)
- ζ m :
-
mean vorticity
- ν:
-
fluid viscosity
References
Chow R, van Dam CP (2006) Unsteady computational investigations of deploying load control microtabs. J Aircraft 43(5):1458–1469
Gerontakos P, Lee T (2006) Oscillating wing loadings with trailing-edge strips. J Aircraft 43(2):428–436
Gerontakos P, Lee T (2008) PIV investigation of flow over unsteady airfoil with trailing-edge strip. Exp Fluids 44(4):539–556
Jeffrey D, Zhang X, Hurst DW (2000) Aerodynamics of Gurney flaps on a single-element high-lift wing. J Aircraft 37(2):295–301
Lee H-K, Kroo IM (2004) Computational investigation of wings with miniature trailing edge control surfaces. AIAA Paper 2004–2693
Liebeck RH (1978) Design of subsonic airfoils for high lift. J Aircraft 15(9):547–561
Meyer R, Hage W, Bechert DW, Schatz M, Thiele F (2006) Drag reduction on Gurney flap by three-dimensional modifications. J Aircraft 43(1):132–140
Myose R, Papadakis M, Heron I (1998) Gurney flap experiments on airfoils, wings, and reflection plane model. J Aircraft 35(2):206–211
Neuhart DH, Pendergraft OC (1988) A water tunnel study of Gurney flaps. NASA TM 4071
Norris G (2008) Key improvement to blended-wing body control. Aviation Week & Space Tech, Jan 14, 36–37
Purser PE, Turner TR (1943) Aerodynamic characteristics and flap loads of perforated double split flaps on a NACA 23012 airfoil. NACA report L-415
Roshko A (1954) On the drag and shedding frequency of two-dimensional bluff bodies. NACA TN-3169
Stanewsky E (2001) Adaptive wing and flow control technology. Prog Aerospace Sci 37:583–667
Storms BL, Jang CS (1994) Lift enhancement of an airfoil using a Gurney flap and vortex generators. J Aircraft 31(3):542–547
Tang D, Dowell EH (2007) Aerodynamic loading of an airfoil with an oscillating Gurney flap. J Aircraft 44(4):1245–1257
Troolin DR, Longmire EK, Lai WT (2006) Time resolved PIV analysis of flow over a NACA 0015 airfoil with Gurney flap. Exp Fluids 41:241–254
Zerihan J, Zhang X (2001) Aerodynamics of Gurney flaps on a wing in ground effect. AIAA J 39(5):772–780
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Lee, T., Ko, L.S. PIV investigation of flowfield behind perforated Gurney-type flaps. Exp Fluids 46, 1005–1019 (2009). https://doi.org/10.1007/s00348-008-0606-1
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DOI: https://doi.org/10.1007/s00348-008-0606-1