![]() Wereley S, Gui L (2001) PIV measurement in a four-roll-mill flow with a central difference image correction (CDIC) method. Using the two-dimensional ARC2D Navier-Stokes flow solver analyses were conducted to predict the sectional aerodynamic characteristics of the flapped NACA-0015 airfoil section. Wadcock A (1987) Investigations of low-speed turbulent separated flow around airfoils. Storms B, Jang C (1994) Lift enhancement of an airfoil using a Gurney flap and vortex generators. Solovitz S, Eaton J (2004b) Dynamic flow response due to motion of partial-span Gurney-type flaps. Solovitz S, Eaton J (2004a) Spanwise response variation for partial-span Gurney-type flaps. Neuhart D, Pendergraft O (1988) A water tunnel study of Gurney flaps. Liebeck R (1978) Design of subsonic airfoils for high lift. Jeffrey D, Zhang X, Hurst D (2000) Aerodynamics of Gurney flaps on a single-element high-lift wing. Jang C, Ross J, Cummings R (1998) Numerical investigation of an airfoil with a Gurney flap. Jacobs E, Sherman A (1937) Airfoil section characteristics as affected by variations of the Reynolds number, NACA Langley Memorial Aeronautical Laboratory (Langley Field, VA, United States), NACA Report 586, pp 41 Jacobs E, Anderson R (1930) Large-scale aerodynamic characteristics of airfoils as tested in the variable density wind tunnel, NACA Langley Memorial Aeronautical Laboratory (Langley Field, VA, United States), NACA TR 352, pp 421–450 Exp Fluids 29:275–290īlake W (1986) Mechanics of flow-induced sound and vibration, vol II. ![]() Meas Sci Technol 8:1393–1398Īdrian R, Christensen K, Liu Z (2000) Analysis and interpretation of instantaneous turbulent velocity fields. Predicted particle traces for the flapped NACA-0015 airfoil (Minf 0.70, (x 9 degrees, 5 -10 degrees, Re 3 million) Predicted Mach number contours for the flapped NACA-0015 airfoil (Minf 0. University of Illinois, Annual Review Fluid Mechanics, vol 23, pp 261–304Īdrian R (1997) Dynamic ranges of velocity and spatial resolution of particle image velocimetry. Comparison of flow around ‘filled’ and ‘open’ flap configurations suggested that the second shedding mode was responsible for a significant portion of the overall lift increment.Īdrian R (1991) Particle-imaging techniques for experimental fluid mechanics. ![]() For a 4% Gurney flap at α = 8°, the first and second modes corresponded with Strouhal numbers based on flap height of 0.18 and 0.13. The second mode, which was caused by the intermittent shedding of fluid recirculating in the cavity upstream of the flap, becomes more coherent with increasing angle of attack. The dominant mode resembles a Kàrmàn vortex street shedding behind an asymmetric bluff body. Two distinct vortex shedding modes were found to exist and interact in the wake downstream of flapped airfoils. The Gurney flap, a tab of small length (1–4% of the airfoil chord) that protrudes perpendicular to the chord at the trailing edge, yields a significant and relatively constant lift increment through the linear range of the C L versus α curve. A NACA 0015 airfoil with and without a Gurney flap was studied in a wind tunnel with Re c = 2.0 × 10 5 in order to examine the evolving flow structure of the wake through time-resolved PIV and to correlate this structure with time-averaged measurements of the lift coefficient. ![]()
0 Comments
Leave a Reply. |
AuthorWrite something about yourself. No need to be fancy, just an overview. ArchivesCategories |