Shock effects on delta wing vortex breakdown

46th AIAA Aerospace Sciences Meeting and Exhibit

Volumn , Issue , 2008, Pages

  Schiavetta, L A ^a   Boelens, O J ^b   Crippa, S ^c   Cummings, R M ^d   Fritz, W ^e   Badcock, K J ^f  

^a UNIVERSITY OF GLASGOW   (United Kingdom)

^b NATIONAL AEROSPACE LABORATORY NLR   (Netherlands)

^c ROYAL INSTITUTE OF TECHNOLOGY   (Sweden)

^d UNITED STATES AIR FORCE ACADEMY   (United States)

^e AIRBUS GROUP INNOVATIONS   (Germany)

^f UNIVERSITY OF LIVERPOOL   (United Kingdom)

Author keywords

[No Author keywords available]

Indexed keywords

COMPUTATIONAL FLUID DYNAMICS; VORTEX FLOW; WINGS;

ANGLE OF INCIDENCE; DELTA WING VORTICES; DELTA WINGS; FREE-STREAM; SHOCK STRENGTH; SHOCK-VORTEX INTERACTION; VORTEX BREAKDOWN LOCATION; VORTEX STRENGTH;

DELTA WING AIRCRAFT;

EID: 78149434306     PISSN: None     EISSN: None     Source Type: Conference Proceeding    
DOI: 10.2514/6.2008-395     Document Type: Conference Paper

References (25)

1. Jobe C.E. Vortex breakdown location over 65° delta wings empiricism and experiment. Aeronautical Journal, pages 475-482, September 2004.
2. Elsenaar A and Hoeijmakers H.W.M. An experimental study of the flow over a sharp-edged delta wing at subsonic and transonic speeds. In AGARD Conference Proceedings "Vortex Flow Aerodynamics", pages 15.1-15.19. AGARD-CP-494, July 1991.
3. Longo J.M.A. Compressible inviscid vortex flow of a sharp edge delta wing. AIAA Journal, 33(4):680-687, April 1995.
4. Thomer O, Schroder W, and Krause E. Normal shock vortex interaction. In Proceedings of the RTO-AVT Symposium on "Advanced Flow Management: Part A - Vortex Flows and High Angle of Attack for Military Vehicles" - RTO-MP-069(I), pages 18.1-8.10. NATO RTO, 2001.
5. Donohoe S.R and Bannink W.J. Surface reflective visualisations of shock-wave/vortex interactions above a delta wing. AIAA Journal, 35(10):1568-1573, October 1997.
6. Elsenaar A, Hjemberg L, Biitefisch K-A, and Bannink W.J. The international vortex flow experiment. In Validation of Computational Fluid Dynamics - AGARD-CP-437 Volume 1, pages 9.19.23. AGARD, 1988.
7. Hummel D and Redeker G. A new vortex flow experiment for computer code validation. In Proceedings of the RTO-AVT Symposium on "Advanced Flow Management: Part A - Vortex Flows and High Angle of Attack for Military Vehicles" - RTO-MP-O69(l), pages 8.1-8.32. NATO RTO, 2001.
8. Hummel D. Effects of boundary layer formation on the vortical flow above slender delta wings. In RTO-MP-AVT-111, pages 30.1-30.22. NATO, October 2004.
9. Chu J and Luckring J.M. Experimental surface pressure data obtained on a 65° delta wing across Reynolds number and Mach number ranges: Volume 1 - sharp leading edge. NASA Technical Memorandum 4645, NASA Langley Research Centre, February 1996.
10. Chu J and Luckring J.M. Experimental surface pressure data obtained on a 65° delta wing across Reynolds number and Mach number ranges: Volume 2 - small radius leading edge. NASA Technical Memorandum 4645, NASA Langley Research Centre, February 1996.
11. Chu J and Luckring J.M. Experimental surface pressure data obtained on a 65° delta wing across Reynolds number and Mach number ranges: Volume 3 - medium radius leading edge. NASA Technical Memorandum 4645, NASA Langley Research Centre, February 1996.
12. Chu J and Luckring J.M. Experimental surface pressure data obtained on a 65° delta wing across Reynolds number and Mach number ranges: Volume 4 - large radius leading edge. NASA Technical Memorandum 4645, NASA Langley Research Centre, February 1996.
13. Boelens O.J. Private communication.
14. Konrath R. Private communication.
15. FLOWer, Installation and User Handbook.
16. Kok J.C. Mathematical physical model of ENSOLV version 3.20; a flow solver for 3D Euler/Navier-Stokes equations in arbitrary multi-block domains. NLR-CR-2000-620, Nationaal Lucht- en Ruimtevaartlaboratorium, NLR, 2000.
17. Kok J.C and Prananta B.B. User guide of ENSOLV version 5.01. a flow solver for 3D Euler/Navier-Stokes equations in arbitrary multi-block domains with aeroelastic capabilities. NLR-CR-2001-348, Nationaal Lucht- en Ruimtevaartlaboratorium, NLR, 2001.
18. Badcock K.J, Richards B.E, and Woodgate M.A. Elements of computational fluid dynamics on block strucured grids using implicit solvers. Progress in Aerospace Sciences, 36:351-392, 2000.
19. Leonard A. Energy cascade in large eddy simulation of turbulent fluid flow. Advances in Geophysics, 18A:237-248, 1974.
20. Houtman E.M and Bannink B.J. Experimental and numerical investigation of the vortex flow over a delta wing at transonic speeds. In AGARD Conference Proceedings "Vortex Flow Aerodynamics", pages 5.1-5.11. AGARD-CP-494, July 1991.
21. Kok J.C. Resolving the dependence on freestream values for the k - ω turbulence model. AIAA Journal, 38(7):1292-1294, 2000.
22. Delery J.M. Aspects of vortex breakdown. Progress in Aerospace Sciences, 30(1):1-59, 1994.
23. Kalkhoran I.M and Smart M.K. Aspects of shock wave-induced vortex breakdown. Progress in Aerospace Sciences, 36:63-95, 2000.
24. Spall R.E, Gatski T.B, and Grosch C.E. A criterion for vortex breakdown. Physics of Fluids, 30(11):3434-3440, November 1987.
25. Robinson B.A, Barnett R.M, and Agrawal S. Simple numerical criterion for vortex breakdown. AIAA Journal, 32(1):116-122, January 1994.