Lift Enhancement Using Static Extended - PDF document

1 Lift Enhancement Using Static Extended
Lift Enhancement Using Static Extended Trailing Edge (SETE) Tianshu Liu and William Liou Western Michigan University Kalamazoo, MI 49008 Qamar Shams NASA Langley Research Center Hamp

2 ton, VA 23681 Extended Trailing Edge
ton, VA 23681 Extended Trailing Edge — A Biologically - Inspired Concept Objectives • Explore the feasibility of improving the aerodynamic performance of airfoils and wings u

3 sing static extended trailing edg
sing static extended trailing edge (SETE) • Understand the physical mechanisms behind lift enhancement of airfoil and wing with static extended trailing edge (SETE)

4 SETE for Lift Enhancement in Cruise Fli
SETE for Lift Enhancement in Cruise Flight Fundamental Aerodynamic Aspects Geometrical Parameters and Coordinate System: Aerodynamic Force Measurements in Wind Tunnels NACA0012 Mode

5 l with SETE: Advanced Design Wind Tunn
l with SETE: Advanced Design Wind Tunnel: Speed: 6 - 73 m/s Test section: 4 by 3 feet Tu: 0.1 - 0.4% Six - component balance Lift Enhancement of NACA0012 by SETE Camber Effect! L/

6 D of NACA0012 with SETE • L/D vs.
D of NACA0012 with SETE • L/D vs. CL curves are collapsed for different deflection angles • Zero - lift drag and Oswald efficiency remain unchanged Lift Enhancement at the Minimum

7 Cost of Increasing Drag in Cruise F
Cost of Increasing Drag in Cruise Flight Comparison with Gurney Flap Comparison with Gurney Flap Comparison between SETE and Gurney Flap SETE and Gurney Flap: Thin Airfoil Theory

8 SETE: where Gurney: Gurney
SETE: where Gurney: Gurney SETE SETE Solution of Generalized Thin Airfoil Integral Equation for Gurney Flap Net Benefit for Power Required in Cruise Flight Criterion for Ac

9 tive Flow Control: Criterion for Idea
tive Flow Control: Criterion for Ideal Passive Flow Control: Cruise Benefit Margin for SETE �(g 0 until AoA = 12 deg ) �g 0 CFD Simulations Comparison of SE

10 TE with Conventional Flap & Gurney Fla
TE with Conventional Flap & Gurney Flap Comparison of SETE, Gurney, and Conventional Flaps SETE SETE 2D CFD 2D CFD Lift Enhancement by SETE at a Small Drag Penalty for Cruise Flig

11 ht Drag polar CL vs. AoA 10%c Al S
ht Drag polar CL vs. AoA 10%c Al SETE Wake Velocity Profiles Re = 50,000 10%c plastic FETE 10%c Al FETE Power Spectrum Vorticity Maps 10%c plastic FETE Wake Change by SETE

12 : Water Tunnel Experiments Baseline NA
: Water Tunnel Experiments Baseline NACA0012 Re = 50,000 x/max(t) = 0.23 x/max(t) = 0.46 x/max(t) = 0.61 x/max(t) = 0.84 x/max(t) = 1.22 x/max(t) = 1.61 Development of Wake Flow

13 Structures in Baseline Model NACA0012
Structures in Baseline Model NACA0012 with a 10% plastic FETE Re = 50,000 x/max(t) = 1.29 x/max(t) = 1.75 x/max(t) = 2.05 x/max(t) = 2.43 x/max(t) = 2.79 x/max(t) = 3.25 Parame

14 tric Space: Development of Wake Flow S
tric Space: Development of Wake Flow Structures Affected by SETE Application of SETE can improve the cruise flight efficiency of transport aircraft and UAV without changing the basic

15 aerodynamic configuration Conclusions
aerodynamic configuration Conclusions • “Lif Enncmn by Sic En Triling Eg,” T. Liu, J. Montefort, W. Liou, S. R. Pantula, and Q.

16 Shams, Journal of Aircraft , Vol. 44,
Shams, Journal of Aircraft , Vol. 44, No. 6, 2007, pp. 1939 - 1947 • “Tin - Airfoil - Theoretical Interpretation for Gurney Flap Lift Enncmn,” T. Liu and J. Montefor

17 t, Journal of Aircraft , Vol. 44, No.
t, Journal of Aircraft , Vol. 44, No. 2, 2007, pp. 667 - 671 • “Wig Cririon on Flow Conrol in Lvl Flig,” T. Liu, Journal of Aircraft , Vol. 44, No. 1, 2

18 007, pp. 348 - 351 • “Flow s
007, pp. 348 - 351 • “Flow s  Cylinr wi  Fling Elmn Ac o is En,” W. W. Liou, S. R. Pantula, T. Liu, J. Montefort,

19 D. Ludens, AIAA Paper 2007 - 1309 , R
D. Ludens, AIAA Paper 2007 - 1309 , Reno, NV, 2007 • “Unsy Flow Clculions for Flibl Tin Pl,” W. W. Liou, S. and R. Pantula, AIAA Paper 2007

20 - 4339 , Miami, FL, 2007 • “Sï
- 4339 , Miami, FL, 2007 • “Sic En Triling Eg for Lif Enncmn: Erimnl n Computational Studies ,” T. Liu, J.

21 Montefort, W. W. Liou, and S. R. Pantul
Montefort, W. W. Liou, and S. R. Pantula, 3rd International Symposium on Integrating CFD and Experiments in Aerodynamics, U.S. Air Force Academy, CO, 20 - 21, June, 2007 Relevant Publications