Asymmetric vortices flow over slender body and its active control at high angle of attack

Erickson GE. High angle-of-attack aerodynamics.Annu Rev Fluid Mech, 1995, 27:45–88 Smith JHB. Vortex flows in aerodynamics.Annu Rev Fluid Mech, 1986, 18: 221–242 Ericsson LE. Challenges in high-alpha vechiele dynamics.Progress in Aerospace Science, 1995, 31: 291–334 Yang GW, Lu XY, Zhuang LX. Vortex control by the spanwise suction flow on the upper surface of delta wing.Acta Mechanica Sinica, 1999, 15(2): 116–125 Zhuang FG. On numerical techniques in CFD.Acta Mechanica Sinica, 2000, 16(3): 193–216 Wardlaw AB Jr. High angle of attack missile aerodynamics. AGARD LS-98, Paper 5, 1978 Sun M, Wu JH. Large aerodynamic force on a sweeping wing at low Reynolds number.Acta Mechanica Sinica, 2004, 20(1): 24–31 Allen HJ, Perkins EW. Characteristics of flow over inclined bodies of revolution. NACA RM A50L07, 1951 Chapman GT, Keener ER. The aerodynamics of bodies of revolution at angles of attack to 90°. AIAA Paper 79-0023, 1979 Hunt BL. Asymmetric vortex forces and wakes on slender bodies. AIAA Paper 82-1336, 1982 Ericsson LE, Reding JP. Vortex-induced asymmetric loads in 2-D and 3-D flows. AIAA Paper 80-0181, 1980 Ericsson LE, Reding JP. Aerodynamics effects of asymmetric vortex shedding from slender bodies. AIAA Paper 85-1797, 1985 Ericsson LE. Control of forebody flow asymmetric-A critical review. AIAA Paper 90-2833, 1990 Ericsson LE, Reding JP. Asymmetric flow separation and vortex shedding on bodies of revolution. In: Progress in Astronautics and Aeronautics. AIAA Vol. 141, chap. 10, 391–452, 1992 Malcolm G. Forebody vortex control—A progress review. AIAA Paper 93-3540, 1993 Williams D. A review of forebody vortex control scenarios. AIAA Paper 97-1967 Ericsson LE, Beyers ME. Fluid mechanics considerations for successful design of forebody flow control. AIAA Paper 2000-2320, 2000 Roos FW. Micro blowing: An effective, efficient method of vortex—asymmetry management. AIAA Paper 2000-4416, 2000 Keener ER, Chapman GT. Onset of aerodynamic side forces at zero sideslip on symmetric fore bodies at high angles of attack. AIAA Paper 74-770, 1974 Peake DJ, Owen FK, et al. Symmetrical and asymmetrical separations about a yawed come. AGARD CP-247 Paper 16, 1979 Stetson KJ, Ojadana ES. Hypersonic laminar boundary layer separation on a slender cone at angle of attack.AIAA Journal, 1972, 10(5): 642–648 Peake DJ, Owen FK, Higuchi H. Symmetrical and asymmetrical separations about a yawed cone. AGARD CP-247, Paper 16, 1978 Keener ER, Chapman GT. Similarity in vortex asymmetries over slender bodies and wings.AIAA Journal, 1977, 15(9): 1370–1372 Ericsson LE. Sources of high alpha vortex asymmetry at zero sideslip.Journal of Aircraft, 1992, 29(6): 1086–1090 Bird JD. Tuft-grid surveys at low speeds for delta wings. NASA TN D 5054, 1969 Stahl WH, Mahmood M, Asghar. Experimental investigations of the vortex flow on delta wings at high incidence.AIAA Journal, 1992, 30(4): 1627–1032 Shanks RE. Low-subsonic measurements of static and dynamic stability derivatives of six flat-plate wings having leading-edge sweep angles of 74° to 84°. NASA TND-1822, 1963 Marconi F. Asymmetric separated flows about sharp cones in a supersonic stream. In: Proceedings of the 11th International Conference on Numerical Methods in Fluid Dynamics, 1998. 395–402 Dyer DE, Fiddes SP, Smith JHB. Asymmetric vortex formation from cones at incidence, a simple inviscid model.Aeronantical Qurt, 1982, 33: 293–312 Cai JS, Liu F, Luo SJ. Stability of symmetric vortices in two dimensions and over three-dimensional slender conical bodies.J Fluid Mech 2003, 480: 65–94 Cai JS, Luo SJ, Liu F. Stability of symmetric and asymmetric vortex pairs over slender conical wings and bodies.Physics of Fluids, 2004, 16(2):424–432 Degani D, Tobak M. Experimental study of controlled tip disturbance effect on flow asgmmetry.Physics of Fluids, 1992, 4(12): 2825–2832 Degani D. Effect of geometrical disturbances on vortex asymmetry.AIAA Journal, 1991, 29(4): 560–566 Degani D. Instability of flows over bodies at large incidence.AIAA Journal, 1992, 30(1): 94–100 Bernhardt JE, Williams DR. Proportional control of asymmetric forebody vortices.AIAA Journal, 1998, 36(11): 2087–2093 Deng XY, Liu PQ, Kong FM.Acta Aerodynamica Sinica, 2000, 18(Supplement): 121–126 (in Chinese) Zhang HX, Ran Z. On the structural stability of the flows over slender at angle of attack.Acta Aerodynamica Sinica, 1997, 15(1): 20–26 (in Chinese) Lamont PJ, Hunt BL. Out-of-plane force on a circular cylinder at large angles of inclination to a uniform stream.Aeronautical Journal, 1973, 69(1): 41–45 Lamont PJ, Hunt BL. Pressure and force distributions on a sharp-nosed circular cylinder at large angles of inclination to a uniform subsonic stream.J Fluid Mech, 1976, 76(3): 519–599 Hunt BL, Dexter PC. Pressure on a slender body at high angle of attack in a very low turbulence level airstream, AGARD-CP-247, Paper No. 17. 1978 Zilliac GG, Degani D, Tobak M Asymmetric vortices on a slender body of revolution.AIAA Journal, 1991, 29(5): 667–675 Wardlaw AB, Morrison AM. Induced side forces at high angles of attack.Journal of Spacecraft and Rocket, 1976, 13(10): 589–593 Keener ER, Chapma GT, Cohen L, et al. Side forces on a tangent—ogive forebody with a fineness ratio of 3.5 at high angles of attack and Mach numbers from 0.1 to 0.7. NASA TM X-3437, 1977 Dexter PC, Hunt BL. The effects of roll angle on the flow over a slender body of revolution at high angles of attack. AIAA Paper 81-0358, 1981 Deng XY, Chen XR, Wang YK, et al. Influence of nose perturbations on behaviors of asymmetric vortices over slender body. AIAA Paper 2002-4710, 2002 Chen XR, Deng XY, Wang YK, et al. Influence of nose perturbations on behavior of asymmetric vortices over slender body.Acta Mechanica Sinica, 2003, 18(b): 581–593 Deng XY, Wang YK, et al. Deterministic flow field and flow structure model of asymmetric vortices over slender body. AIAA Paper 2003-5475, 2003 Deng XY, Wang G, et al. A physical model of asymmetric vortices flow structure in regular state over slender body at high angle of attack.Science in China (series E), 2003, 46(6): 561–573 Liu PQ, Deng XY. Lee-side vortex structure and aerodynamic characteristics analysis over a slender cylinder at high incidence.Acta Mechanica Sinica, 2002, 34(2): 248–255 (in Chinese) Sarpkaya T. Separated flow about lifting bodies and impulsive flow about cylinders.AIAA Journal, 1966, 4(3): 414–420 Thomson KD, Morrison DF. The spacing, position, and strength of vortices in the wake of slender cylindrical bodies at large incidence.J Fluid Mech, 1971, 50(4): 751–783 Moskovitz CA, Hall RM, Dejarnette FR. New device for controlling asymmetric flowfields on forebodies at large alpha.J Aircraft, 1991, 28(7): 456–462 Bridges DH, Hornung HG. Elliptic tip effects on the vortex wake of an axisymmetric body at incidence.AIAA Journal, 1994, 32(7): 1437–1445 Luo SC, Lim TT, et al. Flowfield around ogive/elliptic-tip cylinder at high angle of attack.AIAA Journal, 1998, 36(10): 1778–1787 Yang YG, Cui EJ, Zhou WJ. Numerical studies about an asymmetric vortex flow around a slender body at high incidence.Acta Mechanica Sinica, 2004, 36(1): 1–8 (in Chinese) Ward KC, Katz S. Development of flow structures in the Lee of an inclined body of revolution.Journal of Aircraft, 1989, 26(3): 198–203 Deng XY, Wang G, et al. The study of determinacy and multi-vortex structure of the flow over slender body at high angles of attack. In: Proceedings of 5th National Conference on Flow Visualization, 2002. 6–16 (in Chinese) Alcorn CW, Croom MA, Francis MS. The X-31 experience: aerodynamic impediments to post-stall agility. Cao Y, Deng X. Insight into fuselage aerodynamic forces and strake control at high angles of attack.Canadian Aeronautics and Space Journal, 2000, 46(3): 150–158 Rao DM. Side-force alleviation on slender pointed forebodies at high angles of attack.Journal of Aircraft, 1979, 16(11): 763–768 Keener ER, Chapman GT, cohen L, et al. Side forces on forebody at high angles of attack and Mach numbers from 0.1 to 0.7: Two tangent, paraboloid and cone. NASA TM-X-3437, 1976 Gu YS, Ming X. Forebody vortices control using a fast-swinging micro-tip-strake at high angles of attack.Acta Aeronautics and Astronautics Sinica, 2003, 24(2): 102–106 Fidler SE. Active control of asymmetric vortex effects.Journal of Aircraft, 1981, 18(4): 267–272 Rao DM, Moskovitz C, Murri DG. Forebody votex management for yow control at high angles of attack.Journal of Aircraft, 1987, 24(4): 248–254 Malcolm GN, Ng TT. Aerodynamic control of fighter aircraft by manipulation of forebody vortices. AGARD, CP-497, Paper 15, 1991 Eidson RC, Mosbarger NA. Forebody pneumatic devices at low angles of attack and transonic speed. AIAA Paper 97-0042, Jan 1997 Cornelius RC, Pandit N, et al. An experimental study of pneumatic vortex flow control on high angle of attack forebody model. AIAA Paper 92-0018, 1992 Ng TT, Maleolm GN. Forebody vortex control using small, rotatable strakes.Journal of Aircraft, 1992, 29(4): 671–678 Deng XY. Asymmetric vortices flow and active control with Bleed Perturbatioin. In: Proceedings of KSAS 1st International Sessions, 2003. 75–80 Moskovitz CA, Hall RM, et al. Effects of nose bluntness, roughness and surface perturbations on the asymmetric flow past slender bodies at large angles of attack. AIAA Paper 89-2236, 1989 Williams D, El-Khabiry S, Papazian H. Control of asymmetric vortices around a cone-cylinder geometry with unsteady base bleed. AIAA Paper 89-1004, Mar 1989 Williams D, Papazian H. Forebody vortex control with the unsteady bleed technique.AIAA Journal, 1991, 29(5):853–855 Williams D, Berhhardt J. Proportional control of asymmetric forebody vortices with the unsteady bleed technique. AIAA Paper 90-1629, June 1990 Bernhardt J, Williams DR. The effect of Reynolds number on control of forebody asymmetry by suction and bleed. AIAA Paper 93-3265, July 1993 Roos FW, Mayness CL. Bluntness and blowing for flowfield asymmetry control on slender forebodies. AIAA Paper 93-3409, 1993 Roos FW. Microblowing for high-angle-of-attack vortex flow control on a fighter aircraft. AIAA Paper 96-0543, Jan 1996 Roos FW. Microblowing for vortex asymmetry management on a hemisphere-cylinder forebody. AIAA Paper 96-1951, June 1996 Keener ER. Flow separation patterns on symmetric forebodies. NASA. TM86016, 1986 Lamont PS. Pressures around an inclined ogive cylinder with laminar, transitional, or turbulent separation.AIAA Journal, 1982, 20(11):1492–1499 Bernhardt JE, Williams DR. The effect of Reynolds number on vortex symmetry about slender bodies.Phys Fluids A, 1993, 5(2): 291–293