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Measurements of leading-edge vortices on a 75° delta planform wing at M = 2.5

Published online by Cambridge University Press:  04 July 2016

I. M. Milanovic  and
I. M. Kalkhoran
I. M. Milanovic
Affiliation:
Polytechnic University, Brooklyn New York, USA
I. M. Kalkhoran
Affiliation:
Polytechnic University, Brooklyn New York, USA
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Abstract

An experimental study of the supersonic vortices from a 75° swept-back delta wing has been carried out in a Mach 2.49 stream. Five-hole conical probe surveys were conducted at the trailing edge of the planform for 7° and 12° angles-of-attack. The main objective was to determine the Mach number and pressure distributions in the primary vortex. A novel approach of utilising a computational flow solver was used to generate the calibration data for the five-hole probe over a range of Mach numbers and pitch angles. Measurements indicate significant static and total pressure deficits in the vortex core. Both the magnitude and the spatial scale of these deficits increase with the higher incidence angle. The swirl profiles have supersonic peak magnitudes and resemble the low speed Lamb-Oseen vortex. Similar to the case of supersonic wing tip vortices, and contrary to the experimental results from transonic and low speed leading-edge vortices, the axial Mach number distribution in the vortex core is found to have strong wake-like profile.

Type
Research Article
Information
The Aeronautical Journal , Volume 106 , Issue 1055 , January 2002 , pp. 39 - 49
Copyright
Copyright © Royal Aeronautical Society 2002 

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References

1. Green, S.I. (Ed) Fluid vortices, Fluid Mechanics and its Applications, Kulwer Academic Publishers, Dordrecht, 1995, 1st ed, 30.Google Scholar
2. Sforza, P.M. Aircraft Vortices: Benign or Baleful?, Space/Aeronautics, 1970, 53, pp 42–48.Google Scholar
3. Monnerie, B. and Werlé, H. Study of supersonic and hypersonic flow about a slender wing at an angle-of-attack, hypersonic boundary layers and flow fields, AGARD CP–30, 1968, pp 23–1–23–19.Google Scholar
4. Rom, J. High Angle-of-Attack Aerodynamics, Springer-Verlag, New York, 1992, 1st ed.Google Scholar
5. Stromberg, A., Henze, A., Limberg, W. and Krause, E. Investigation of vortex structures on delta wings, Zeitschrift für Flugwissenschaften und Weltraumforschung, 1996, 20, (2), pp 71–79.Google Scholar
6. Gad-El-Hak, M. and Blackwelder, R. The discrete vortices from a delta wing, AIAA J, 1985, 23, (6), pp 901–902.Google Scholar
7. Brown, G.L. and Roshko, A. On density effects and large structure in turbulent mixing layers, J Fluid Mechanics, 1974, 64, pp 775–816.Google Scholar
8. Winant, C.D. and Browand, F.K. Vortex pairing: the mechanism of turbulent mixing-layer growth at moderate Reynolds number, J Fluid Mechanics, 1974, 63, pp 237–255.Google Scholar
9. Caricaillet, R., Manie, F., Pagan, D. and Solignac, J. Leading-edge vortex flow over a 75 degree swept delta wing — experimental and computational results, proceedings of 15th ICAS Congress, 1986, Paper No 86–1.5.1, pp 589–603.Google Scholar
10. Ganzer, U. and Szodruch, J. Vortex formation over delta, double-delta and wave rider configurations at supersonic speeds, AGARD-CP–428, 1987, pp 25–1–25–32.Google Scholar
11. Smith, L.G., Maurice, M.S., Seibert, G.L. and Tyler, C. Laser velocimetry measurements of supersonic vortex flows on a simple razor-edged delta wing, AIAA June 1991, Paper 91–1684.Google Scholar
12. Lang, N. PIV measurements in sub- and supersonic flow over the delta wing configuration ELAC, proceedings of the 8th International Symposium on Flow Visualisation, Sorrento, Italy, September 1998, pp 205.1–205.8.Google Scholar
13. Brodetsky, M.D. and Shevchenko, A.M. Some features of a separated flow and supersonic vortex structure at the leeside of a delta wing, Separated Flows and Jets, Kozlov, V.V. and Dovgal, A.V. (Eds), IUTAM Symposium Novosibirsk, Springer-Verlag, Berlin Heidelberg, 1991.Google Scholar
14. Centolanzi, F.J. Characteristics of a 40 deg cone for measuring Mach number, total pressure and flow angles at a supersonic speeds, NACA-TN- 3967, May 1957.Google Scholar
15. Gaillard, R. Calibration and use of an ONERA miniature five hole probe, 7th Symposium on Measuring Techniques for Transonic and Supersonic Flow in Cascades and Turbomachines, Aachen, Germany, 1983.Google Scholar
16. Brodetsky, M.D. and Shevchenko, A.M. Methodological investigation of multichannel flow-angularity probes for the determination of the direction and Mach number of a three-dimensional flow, Inst of Theoretical and Applied Mechanics, 1987, Preprint 31–87, USSR Academy of Sciences, Novosibirsk, Russia.Google Scholar
17. Smart, M.K, Kalkhoran, I.M. and Bentson, J. Measurements of supersonic wing tip vortices, AIAA J, 1995, 33, (10), pp 1761–1768.Google Scholar
18. Krasnov, N.F. Aerodynamics of Bodies of Revolution, Elsevier, New York, 1970.Google Scholar
19. Kalkhoran, I.M., Cresci, R.J. and Sforza, P.M. Development of polytechnic university’s supersonic wind tunnel facility, AIAA January 1993, Paper 93–0798.Google Scholar
20. Vatsa, V.N. and Wedan, W.W. Development of a multigrid code for 3D Navier-Stokes equations and its application to a grid-refinement study, Computers and Fluids, 1990, 18, (4), pp 391–403.Google Scholar
21. Vatsa, V.N., Turkel, E. and Abolhassani, J.S. Extension of multigrid methodology to supersonic/hypersonic 3D viscous flows, NASA Contractor Report 187612, August 1991.Google Scholar
22. Mitcheltree, R.A., Moss, J.N., Cheatwood, F.M., Green, F.A. and Braun, R.D. Aerodynamics of the Mars microprobe entry vehicles, AIAA, August 1997, Paper 97–3658.Google Scholar
23. Turkel, E. and Vatsa, V.N. Effect of artificial viscosity on three dimensional flow solutions, AIAA J, 32, No 1, 1994, pp 39–45.Google Scholar
24. Marconi, F. Private communication, Northrop Grumman Corporate Research Center. Bethpage, NY, 1997.Google Scholar
25. Naughton, J.W., Cattafesta, L.N. and Settles, G.S. Miniature, fast-response 5-hole conical probe for supersonic flowfield measurement, AIAA J, 1993, 31, (3), pp 453–458.Google Scholar
26. Smart, M.K. and Kalkhoran, I.M. The effect of shock strength on oblique shock wave-vortex interaction, AIAA J, 1995, 33, (11), pp 2137–2143.Google Scholar
27. Stanbrook, A. and Squire, L.C. Possible types of flow at swept leading edges, Aeronaut Q, 1964, 15, pt 1, pp 72–82.Google Scholar
28. Szodruch, J.G. and Peake, D.J. Leeward flow over delta wings at supersonic speeds, NASA-TM–81187, April 1980.Google Scholar
29. Miller, D.S. and Wood, R.M. Leeside flows over delta wings at supersonic speeds, J Aircr, 1984, 21, (9), pp 680–686.Google Scholar
30. Seshadri, S.N. and Narayan, K.Y. Possible types of flow on lee surface of delta wings at supersonic speeds, Aeronaut J, 1988, 92, pp 185–199.Google Scholar
31. Hummel, D. On the vortex formation over a slender wing at large angles of incidence, high angle-of-attack aerodynamics, AGARD CP–247, 1978, pp 13–1 - 13–17.Google Scholar
32. Payne, F.M., Ng, T.T. and Nelson, R.C. Seven hole probe measurement of leading edge vortex flows, Experiments in Fluids 7, 1989, pp 1–8.Google Scholar
33. Seshadri, S.N. and Bütefisch, K.A. Evaluation of LDA 3-component velocity data on a 65° delta wing at M = 0.85 and first results and analysis, DFVLR-FB 89–19, Göttingen, March 1989.Google Scholar
34. Donohoe, S.R. Vortex Flow and Vortex Breakdown above a Delta Wing in High Subsonic Flow: an experimental investigation, PhD Thesis, Delft University of Technology, the Netherlands, 1996.Google Scholar
35. Fellows, K.A. and Carter, E.C. Results and analysis of pressure measurements on two isolated slender wings and slender wing-body combinations at supersonic speeds, ARA Report No 12, November 1969.Google Scholar
36. Miller, D.S. and Wood, R.M. Lee-side flow over delta wings at supersonic speeds, NASA Technical Paper 2430, 1985.Google Scholar
37. Longo, J.M.A. Compressible inviscid vortex flow of a sharp edge delta wing, AIAA J, 1995, 33, (4), pp 680–687.Google Scholar
38. Saffman, P.G. Vortex dynamics, Cambridge Monographs on Mechanics and Applied Mathematics, 1992.Google Scholar
39. McMillin, S.N., Thomas, J.L. and Murman, E.M. Navier-Stokes and Euler solutions for lee-side flows over supersonic delta wings, NASA Technical Paper 3035, 1990.Google Scholar
40. Powell, K.G. Vortical Solutions of the Conical Euler Equations, Notes on Numerical Fluid Mechanics, 1990, 28.Google Scholar
41. Jeong, J. and Hussain, F. On the identification of a vortex, J Fluid Mech, 1995, 285, pp 69–94.Google Scholar
42. Gad-El-Hak, M. and Blackwelder, R.F. Control of the discrete vortices from a delta wing, AIAA J, 1987, 25, (8), pp 1042–1049.Google Scholar
43. Verhaagen, N.G. and Kruisbrink, A.C.H. Entrainment effect of a leading-edge vortex, AIAA J, 1987, 25, (8), pp 1025–1032.Google Scholar
44. Visser, K.D. and Nelson, R.C. Measurements of circulation and vorticity in the leading-edge vortex of a delta wing, AIAA J, 1993, 31, (1), pp 104–111.Google Scholar
45. Menke, M. and Gursul, I. Unsteady nature of leading-edge vortices, Physics of Fluids, 1997, 9, (10), pp 2960–2966.Google Scholar
46. Falatyn, P.D. Measurements in the vortical flow over a delta wing at high speed, VKI PR 1987–17, June 1987.Google Scholar
47. Sarpkaya, T. Decay of wake vortices of large aircraft, AIAA J, 1998, 36, (9), pp 1671–1679.Google Scholar