Drag prediction and transition in hypersonic flow

28th Fluid Dynamics Conference

Volumn , Issue , 1997, Pages

  Reed, Helen L ^a   Kimmel, Roger ^b   Schneider, Steven ^c   Arnal, Daniel ^d  

^a Arizona State University   (United States)

^b AIR FORCE RESEARCH LABORATORY   (United States)

^c PURDUE UNIVERSITY   (United States)

^d ONERA   (France)

Author keywords

[No Author keywords available]

Indexed keywords

ANGLE OF ATTACK; FLUID DYNAMICS; HYPERSONIC FLOW; WIND TUNNELS;

DRAG PREDICTION; FLIGHT DATA; LEADING-EDGE CONTAMINATIONS; NOISE LEVELS; NOSE BLUNTNESS; TRANSITION DATA; VISCOUS DRAG;

DRAG;

EID: 84964273486     PISSN: None     EISSN: None     Source Type: Conference Proceeding    
DOI: None     Document Type: Conference Paper

References (99)

1. Adam, P.H. and H.G. Homung, “Enthalpy effects on hypervelocity boundary layer transition: experiments and free flight data”, AIAA Paper 97-0764, 1997.
2. Arnal, D., “Predictions based on linear theory”, AGARD Rep. No. 793 (Special course on progress in transition modelling), Von Karman Inst., Rhode-St.-Genese, Belg., 1994.
3. Arnal, D., E. Kufner, I. Oye, and Ph. Tran, “PROGRAMME TRP TRANSITION: computational results for transition prediction”, Study Note 7, 1996.
4. Arnal, D., F. Vignau, and F. Laburthe, “Recent supersonic transition studies with emphasis on the swept cylinder case”, Conf. on Boundary Layer Transition and Control, Cambridge, April 1991.
5. Beckwith, I.E., T.R. Creel, F.-J. Chen, and J.M. Kendall, “Freestream noise and transition measurements on a cone in a Mach 3.5 pilot low-disturbance tunnel”, NASA TP-2180, 1983.
6. Beckwith, I.E. and C.G Miller HI, “Aerothermodynamics and transition in highspeed wind tunnels at NASA Langley”, Annual Reviews of Fluid Mechanics, v. 22, pp. 419-439, 1990.
7. Beckwith, I., F. Chen, S. Wilkinson, M. Malik, and D. Tuttle, “Design and operational features of low-disturbance wind tunnels at NASA Langley for Mach numbers from 3.5 to 18”, AIAA Paper 90-1391, 1990.
8. Bergstrom, E.R. and S. Raghunathan, “Nonstationarity in gun tunnel flows”, AIAA Journal v. 15 n. 9, pp. 1362-1364, September 1977.
9. Bergstrom, E.R., “A correlation of Mach-7 boundary layer transition data from the Loughborough gun tunnel”, Report TT-7904, Loughborough Univ. of Technology, October 1979. Available from NASA STI as citation 80N28332.
10. Bestek, H., A. Thumm, and H.F. Fasel, “Numerical investigation of later stages of transition in transonic boundary layers”, First European Forum on Laminar Flow Technology, 16-18 March, Hamburg, Germany, 1992a.
11. Bestek, H., A. Thumm, and H.F. Fasel, ‘Direct numerical simulation of the three-dimensional breakdown to turbulence in compressible boundary layers”, 13th International Conference on Numerical Methods in Fluid Dynamics, 6-10 July, Rome, Italy, 1992b.
12. Burke, G. L., “Heat transfer and pressure distributions about sharp and blunt elliptic cones at angles of attack and high Mach numbers”, Air Force Flight Dynamics Laboratory Technical Report AFFDL-TR-64-172, May 1965.
13. Burns, K. A., KJ. Deters, C.P. Haley, and T.A. Khilken, “Viscous effects on complex configurations”, Air Force Wright Laboratory Technical Report WL -TR-3059, August 1995.
14. Bushnell, D.M., “Notes on the initial disturbance fields for the transition problem”, in Instability and Transition, vol. 1, ed. by M.Y. Hussaini and R.G. Voigt, Springer-Verlag, pp. 217-232, 1990.
15. Cattafesta, L. N., V. Iyer, J.A. Masaad, R.A. King, and J.R. Dagenhart, “Three-dimensional boundary- layer transition on a swept wing at Mach 3.5”, AIAA Journal, v. 33, n. 11, pp. 2032-2037, November 1995.
16. Chang, C.-L. and M.R. Malik, “Non-parallel stability of compressible boundary layers”, AIAA Paper 93-2912, 1993.
17. Chen, F.-J., M.R. Malik, and I.E. Beckwith, “Comparison of boundary layer transition on a cone and flat plate at Mach 3.5”, AIAA Paper 88-0411, 1988.
18. Chen, F.-J., M.R. Malik, and I. E. Beckwith, “Boundary-layer transition on a cone and flat plate at Mach 3.5”, AIAA Journal v. 27 n. 6, pp. 687-693, June 1989.
19. Chen, F.-J., “Boundary-layer transition extent measurements on a cone and flat plate at Mach 3.5”, AIAA Paper 93-0342,1993.
20. Demetriades, A., “Hydrodynamic stability and transition to turbulence in a hypersonic boundary layer over a sharp cone”, Air Force Office of Scientific Research AFOSR TR-75-1435, July 1975.
21. Donaldson, J. and S. Coulter, “A review of freestream flow fluctuation and steady-state flow quality measurements in the AEDC/VKF supersonic tunnel A and hypersonic tunnel B”, AIAA Paper 95-6137,1995.
22. Dryden, H. L., “Review of published data on the effect of roughness on transition from laminar to turbulent flow”, J. Aero. Sci., vol. 20, pp. 477-482, July 1953.
23. Dryden, H. L., “Transition from laminar to turbulent flow”, pp. 3-74 in ‘Turbulent flows and heat transfer”, vol. V in the series on High Speed Aerodynamics and Heat Transfer, Princeton Univ. Press, 1959, edited by C.C. Lin.
24. Finley, D., “Hypersonic aerodynamics considerations and challenges”, AIAA Paper 90-5222,1990.
25. Fischer, M. C., “Turbulent bursts and rings on a cone in helium at Me=7.6”, AIAA Journal, v. 10, n. 10, pp. 1387-1389, October 1972.
26. Fischer, M.C. and R.D. Wagner, “Transition and hotwire measurements in hypersonic helium flow”, AIAA Journal v. 10, n. 10, pp. 1326-1332, October 1972.
27. Fisher, D.F. and N.S. Dougherty, Jr., “Flight and wind- tunnel correlation of boundary-layer transition on the AEDC transition cone”, paper 5 in AGARD CP-339, Ground/Flight Test Techniques and Correlation, A symposium held at Cesme, Turkey, October 1982. Also NASA TM 84902, November 1982a.
28. Fisher, D.F. and N.S. Dougherty, Jr., “In-flight transition measurement on a 10-deg. cone at Mach numbers from 0.5 to 2.0”, NASA TP-1982b.
29. Gasperas, G., “Stability of the laminar boundary layer for an imperfect gas”, in Laminar-Turbulent Transition, ed. D. Arnal, R. Michel, pp. 291-302. Berlin: Springer-Verlag, 1990.
30. Haigh, W.W., B.M. Lake, and D.R.S. Ko, “Analysis of flight data on boundary layer transition at high angles of attack”, NASA CR-1913, April 1972.
31. Haynes, T.S., H.L. Reed, and W.S. Saric, “CFD validation and verification questions in transition modelling”, AIAA Paper 96-2051, 1996.
32. He, Y. and R.G. Morgan, “Transition of compressible high enthalpy boundary layer flow over a flat plate”, Aeronautical Journal, v. 98, n. 972, pp. 25-34, 1994.
33. Herbert, Th., “Parabolized stability equations”, Annual Review of Fluid Mechanics, v. 29, p. 245-284, 1997.
34. Herbert, Th., G.K. Stuckert, and N. Lin, “Method for transition prediction in high-speed boundary layers”, Air Force Wright Laboratory WITR- 93-3097, 1993.
35. Holden, M.S., D.R. Bower, and K.M. Chadwick, “Measurements of boundary layer transition on cones at angle of attack for Mach numbers from 11 to 13”, Calspan-University of Buffalo Research Center Report to University of Dayton Research Institute, May 1994.
36. Holden, M. and K. Chadwick, “Studies of laminar, transitional, and turbulent hypersonic flows over curved compression surfaces”, AIAA Paper 95-0093, 1995.
37. Kendall, J. M., “Wind tunnel experiments relating to supersonic and hypersonic boundary-layer transition”, AIAA Journal, Vol. 13, No. 3, 1975, pp. 290-299; also AIAA Paper 74-133, 1974.
38. Kendall, J. M., “Boundary layer receptivity to freestream turbulence”, AIAA Paper 90-1504, 1990.
39. Kimmel, R.L., “Experimental transition zone lengths in pressure gradient in hypersonic flow”, in Transitional and Turbulent Compressible Flows, ASME FED v. 151, pp. 117-127, 1993.
40. Kimmel, R. L. and J. Poggie, “Disturbance evolution / breakdown to turbulence in a hypersonic boundary layer: ensemble averaged structure”, AIAA Paper 97-0555, 1997a.
41. Kimmel, R. L. and J. Poggie, “Transition on an elliptic cone at Mach 8”, ASME Third Symposium on Transitional and Turbulent Compressible Flows, 1997b.
42. Kimmel, R.L., S.N. Schwoerke, and M.A. Klein, “Three-dimensional hypersonic laminar boundary layer computations for transonic experiment design”, AIAA Paper 96-2080, 1996.
43. King, R.A., “Mach 3.5 boundary layer transition on a cone at angle of attack”, AIAA Paper 91-1804, 1991.
44. King, R.A., “Mach 3.5 boundary layer transition on a cone at angle of attack”, AIAA Paper 91- 1804, 1991.
45. Kleiser, L. and T.A. Zang, “Numerical simulation of transition in wall-bounded shear flows”, Annual Review of Fluid Mechanics, v. 23, pp. 495-537, 1991.
46. Kosinov, A.D., A.A. Maslov, and S.G. Shevelkov, “Experiments on the stability of supersonic laminar boundary layers”, Journal of Fluid Mech., v. 219, pp. 621-633, 1990.
47. Lachowicz, J.T., N. Chokani, and J.P. Wilkinson, “Hypersonic boundary layer stability over a flared cone in a quiet tunnel”, AIAA Paper 96- 0782, 1996.
48. Laufer, J., “Aerodynamic noise in supersonic wind tunnels”, J. Aero. Sci., v. 28, pp. 685-692, Sept. 1961.
49. Lyttle, I.J. and H.L. Reed, “Use of transition correlations for three-dimensional boundary layers within hypersonic flows”, Second Symposium on Transitional and Turbulent Compressible Flows, 1995 Joint ASME/JSME Fluids Engineering Conference, August 1995.
50. Mack, L.M., “Boundary-layer linear stability theory”, Special Course on Stability and Transition of Laminar Flows, edited by R. Michel, AGARD Report No. 709, pp. 3-1 to 3-81, 1984.
51. Mack, L.M., “Boundary-layer stability analysis for sharp cones at zero angle-of-attack”, Air Force Wright Aeronautical Laboratory Technical Report AFWAL-TR-86-3022, Aug. 1986.
52. Maddalon, D.V. and A. Henderson Jr., “Boundaiy-layer transition on sharp cones at hypersonic Mach numbers”, AIAA Journal v. 6, n. 3, pp. 424-431, March 1968.
53. Malik, M.R., “Prediction and control of transition in hypersonic boundary layers”, AIAA Paper 87-1414, 1987.
54. Malik, M.R., “Transition in hypersonic boundary layers”, in Numerical and Physical Aspects of Aerodynamic Flows IV, ed. T. Cebeci. New York: Springer, 1989.
55. Malik, M.R., “Stability theory for chemically reacting flows”, in Laminar-Turbulent Transition, ed. D. Amal, R. Michel, pp. 251-60. Berlin: Springer-Verlag, 1990.
56. Malik, M.R., T. Zang, and D.M. Bushnell, “Boundary layer transition in hypersonic flows”, AIAA Paper 90-5232, 1990.
57. Morrisette, E.L., “Roughness induced transition criteria for space shuttle-type vehicles”, Journal of Aircraft, v. 13, n. 2, 1976.
58. Morrisette, E.L., T.R. Creel, and F.-J. Chen, “Effects of cone surface waviness on transition in quiet and noisy supersonic freestreams”, AIAA Paper 86-1086, 1986.
59. Morrisette, E.L. and T. R. Creel, ‘The effects of wall surface defects on boundary-layer transition in quiet and noisy supersonic flow”, in Research in Natural Laminar Flow and Laminar Flow Control, NASA CP-2487, part 3, pp. 965-980, 1987.
60. Murrow, H.N., W.E. McCain, and R. Rhyne, ‘Tower spectral measurements of clear-air turbulence to long wavelengths for altitudes up to 14,000 meters”, NASA TP-1979, 1982.
61. Owen, F.K. and C.C. Horstman, “Hypersonic transitional boundary layers”, AIAA Journal, v. 10, n. 6, pp. 769-775, 1972.
62. Pate, S.R. and C.J. Schueler, “Radiated aerodynamic noise effects on boundary-layer transition in supersonic and hypersonic wind tunnels”, AIAA. Journal, v. 7, n. 3, pp. 450-457, March 1969.
63. Pate, S.R., “Supersonic boundary-layer transition: effects of roughness and freestream disturbances”, AIAA Journal v. 9, n. 5, pp. 797-803, May 1971.
64. Pate, S.R., “Dominance of radiated aerodynamic noise on boundary-layer transition in supersonic/ hypersonic wind tunnels”, AEDC-TR-77-107. DTIC citation AD-A052621, March 1978.
65. Pfenninger, W., “Flow phenomena at the leading edge of swept wings”, AGARDograph 97, Part 4, 1965.
66. Poggie, J. and R.L. Kimmel, “Disturbance evolution / breakdown to turbulence in a hypersonic boundary layer: instantaneous structure”, AIAA Paper 97-0556, 1997.
67. Poll, D.I.A., “Some aspects of the flow near a swept attachment line with particular reference to boundary layer transition”, Technical Report 7805/K, Cranfield, College of Aeronautics, 1978.
68. Poll, D.I.A., “Boundary layer transition on the windward face of space shuttle during reentry”, AIAA Paper 85-0899,1985.
69. Pruett, C.D. and C.-L. Chang, “Spatial direct numerical simulation of high-speed, boundary-layer flows part II: transition on a cone in Mach 8 flow”, Theoretical and Computational Fluid Dynamics, v. 7, n. 5, pp. 397-424, 1995.
70. Pruett, C.D. and T.A. Zang, “Direct numerical simulation of laminar breakdown in highspeed, axisymmetric boundary layers”, Theoretical and Computational Fluid Dynamics, v. 3, n. 6, pp. 345-367, 1992.
71. Reed, H.L., “Direct numerical simulation of transition: the spatial approach”, AGARD Rep. No. 793 (Special course on progress in transition modelling), Von K£rm£n Inst., Rhode-St.- Genese, Belg., 1994.
72. Reed, H.L. and T.S. Haynes, “Transition correlations in 3-D boundary layers”, AIAA Journal, v. 32, pp. 923-29, 1994.
73. Reed, H.L., W.S. Saric, and D. Arnal, “Linear stability theory applied to boundary layers”, Annual Review of Fluid Mechanics, v. 21, pp. 235-284, 1996.
74. Reshotko, E., “Stability theory as a guide to the evaluation of transition data”, AIAA Journal, v. 7, n. 6, pp. 1086-1091, 1969; also AIAA Paper 68-669, 1968.
75. Ross, D.H., J.W. Ellinwood, and R.L. Varwig, “Hypersonic shock tunnel transition studies”, paper 8 in the Proceedings of the Boundaiy Layer Transition Workshop Held 3-5 November 1971, ed. by W.D. McCauley, Aerospace Corp. Report TOR-Ol72(S2816- 16)-5, accession number AD909223 in the Defense Technical Information Center of the USA, also NASA Recon citation 91N71710, 1971.
76. Rumsey, C.B. and D.B. Lee, “Measurements of aerodynamic heat transfer and boundaiy-layer transition on a 15-degree cone in free flight at supersonic Mach numbers up to 5.2”, NASA TN-D-888, August 1961. Supersedes NACA RM L56F26.
77. Schneider, S.P. and C.E. Haven, “Quiet-flow Ludwieg tube for high-speed transition research”, AIAA Journal, v. 33, n. 4, pp. 688-693, April 1995.
78. Small, W.J., F.S. Kirkham, and D.E. Fetterman, “Aerodynamic characteristics of a hypersonic transport configuration at Mach 6.86”, NASA Technical Note NASA TN D-5885, June 1970.
79. Softley, E.J., B. C. Graber, and R. E. Zempel, “Experimental observation of transition of the hypersonic boundary layer”, AIAA Journal, v. 7, n. 2, pp. 257-263, February 1969.
80. Spina, E.F., J.F. Donovan, and A.J. Smits, “On the structure of high-Reynolds-number supersonic turbulent boundary layers”, Journal of Fluid Mechanics, v. 222, pp. 293-327, 1991.
81. Stainback, P.C. and R.D. Wagner, “A comparison of disturbance levels measured in hypersonic tunnels using a hot-wire anemometer and a pitot pressure probe”, AIAA Paper 72-1003, 1972.
82. Sternberg, J., “A free-flight investigation of the possibility of high Reynolds number supersonic laminar boundary layers”, J. Aero. Sci., v. 19, n. 11, pp. 721-733, November 1952.
83. Stetson, K.F., “Mach 6 experiments of transition on a cone at angle of attack”, J. Spacecraft Rockets, v. 19, n. 5, pp. 397-403, 1982.
84. Stetson, K.F., “Hypersonic transition testing in wind tunnels”, in “Instability and Transition”, Proceedings of a Workshop held in Hampton, VA, May 1989, volume I, edited by M.Y. Hussaini and R.G. Voigt, Springer-Verlag, New York, pp. 91-100, 1990.
85. Stetson, K.F. and R.L. Kimmel, “On hypersonic boundary-layer stability”, AIAA Paper 92- 0737, 1992.
86. Stetson, K.F., E.R. Thompson, J.C. Donaldson, and L.G. Siler, “Laminar boundary layer stability experiments on a cone at Mach 8 - Part 2: blunt cone”, AIAA Paper 84-0006, 1984.
87. Stetson, K.F., E.R. Thompson, J.C. Donaldson, and L.G. Siler, “Laminar boundary layer stability experiments on a cone at Mach 8 - Part 3: sharp cone at angle of attack”, AIAA Paper 85- 0492, 1985.
88. Stetson, K.F., E.R. Thompson, J.C. Donaldson, and L.G. Siler, “Laminar boundary layer stability experiments on a cone at Mach 8 - Part 4: on unit Reynolds number and environmental effects”, AIAA Paper 86-1087,1986.
89. Stuckert, G.K., “Linear stability theory of hypersonic, chemically reacting viscous flows”, Ph.D. Dissert. Dept. Mech. Aerosp. Eng., Ariz. State Univ., Tempe, USA, 1991.
90. Stuckert, G.K. and H.L. Reed, “Linear disturbances in hypersonic, chemically reacting shock layers”, AIAA J., v. 32, n. 7, pp. 1384-93, 1994.
91. Thompson, R.A., E.V. Zoby, K.E. Wurster, and P.A. Gnoffo, “Aerothermodynamic study of slender conical vehicles”, J. of Thermophysics and Heat Transfer”, v. 3, n. 4, pp. 361-367, October 1989.
92. Thumm, A., W. Wolz, and H.F. Fasel, “Numerical simulation of spatially growing three- dimensional disturbance waves in compressible boundary layers”, in Laminar-Turbulent Transition, (Arnal, D. and Michel, R., eds.), Springer-Verlag, Berlin, 1990.
93. Tran, Ph., A. Seraudie, V. Wendt, and D.I.A. Poll, “PROGRAMME TRP TRANSITION: experimental results for transition prediction”, Study Note 6, 1995.
94. Watmuff, J.H., “Interactions between Klebanoff modes and TS waves in a Blasius boundary layer’5, AIAA Paper 97-0558, 1997.
95. Wilkinson, S.P., S.G. Anders, F.-J. Chen, and J.A. White, “Status of NASA Langley quiet-flow facility developments”, AIAA Paper 94-2498, 1994.
96. Williamson, W.E., “Hypersonic flight testing”, AIAA Paper 92-3989, 1992.
97. Wlezien, R.W., “Measurement of acoustic receptivity”, AIAA Paper 94-2221,1994.
98. Wright, R. L. and E.V. Zoby, “Flight boundary layer transition measurements on a slender cone at Mach 20”, AIAA Paper 77-719,1977.
99. Zhong, X., “Direct numerical simulation of hypersonic boundary-layer transition over blunt leading edges, Part II: Receptivity to sound”, AIAA Paper 97-0756, 1997.