1. 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. © Experimental And Numerical Investigation Of 65 Degree Delta And 65/40 Degree Double-Delta Wings Al-Garni, AZ; Saeed, F; Al-Garni, AM AMER INST AERONAUT ASTRONAUT, JOURNAL OF AIRCRAFT; pp: 71-76; Vol: 45 King Fahd University of Petroleum & Minerals http://www.kfupm.edu.sa Summary In this study, an experimental and numerical investigation was carried out to obtain lift, drag, and pitching moment data on 65 degree delta and 65/40 degree double-delta wings. The experimental tests were conducted at the King Fahd University of Petroleum and Minerals low-speed wind-tunnel facility, whereas the numerical tests were performed using the commercial computational fluid dynamics software FLUENT. Results from both experiments and numerical predictions were compared to other experimental data found in literature as well as to the theory of Polhamus. The results of comparison of surface pressure coefficient distribution and vortex breakdown location show good agreement with experiments. Overall,, the comparison of result shows good agreement between different experimental studies as well as good agreement with the computational fluid dynamics predictions and the theoretical calculations. References: ALGARNI AZ, 2001, CANADIAN AERONAUTICS, V47, P85 BRENNENSTUHL U, 1982, C INT COUNC AER SCI, P1133 EARNSHAW PB, 1964, 3424 AER RES COUNC EKATERINARIS JA, 1994, AIAA J, V32, P2471 EKATERINARIS JA, 1995, J AIRCRAFT, V32, P457 ERICSSON LE, 1999, J AIRCRAFT, V36, P349 FUJII K, 1988, J NUMERICAL METHODS, V8, P1319 GAI SL, 2004, AERONAUT J, V108, P27 GRISMER DS, 1995, J AIRCRAFT, V32, P1303 HEBBAR SK, 1996, J AIRCRAFT, V33, P743 Copyright: King Fahd University of Petroleum & Minerals; http://www.kfupm.edu.sa

2. 11. 12. 13. 14. 15. 16. 17. 18. 19. 20. 21. 22. 23. 24. 25. 26. 27. 28. 29. 30. 31. 32. 33. 34. 35. 36. 37. 38. 39. © HEBBAR SK, 2000, EXP FLUIDS, V28, P206 HOEIJMAKERS HWM, 1983, J AIRCRAFT, V20, P825 HSU CH, 1988, J AIRCRAFT, V25, P442 HSU CH, 1988, J AIRCRAFT, V25, P675 HSU CH, 1990, AIAA J, V28, P961 HSU CH, 1992, FLUID DYNAMICS RES, V10, P399 JONES RT, 1960, HIGH SPEED WING THEO LAN CE, 1986, VORTEX FLOW AERODYNA, V1, P65 LAUNDER BE, 1972, LECT MATH MODELS TUR LAUNDER BE, 1974, COMPUTER METHODS APP, V3, P269 MANOR D, 1985, J AIRCRAFT, V22, P78 MENTER FR, 1994, AIAA J, V32, P1598 POLHAMUS E, 1996, D3767 NASA TN POLHAMUS EC, 1971, D6243 NASA TN POLHAMUS EC, 1971, J AIRCRAFT, V8, P193 PUCKETT AE, 1947, J AERONAUT SCI, V14, P567 PURVIS JW, 1981, J AIRCRAFT, V18, P225 SHIH TH, 1995, COMPUT FLUIDS, V24, P227 SOHN MH, 2004, J AIRCRAFT, V41, P231 SPALART P, 1992, 920439 AIAA STRAKA WA, 1994, J AIRCRAFT, V31, P688 VERHAAGEN NG, 1985, FLOW VISUALIZATION 3, P652 VERHAAGEN NG, 2001, J AIRCRAFT, V40, P290 WENTZ WH, 1969, 69779 AIAA WENTZ WH, 1971, J AIRCRAFT, V8, P156 WILCOX DC, 1998, TURBULENCE MODELING WOOD RM, 1985, 2433 NASA TP, P120 YAKHOT V, 1986, J SCI COMPUT, V1, P3 YIN XY, 1989, AIAA J, V27, P1313 For pre-prints please write to: abstracts@kfupm.edu.sa Copyright: King Fahd University of Petroleum & Minerals; http://www.kfupm.edu.sa