6Kandil O A, Menzies M A. Effective control of computational simulated wing rock in subsonic flow[R].AIAA 97-0831,1997.
7Gainer T G.A discrete-vortex method for studying the wing rock of delta wing[R]. NASA/TP-2002-211965,2002.
8X.Z.Huang, T.C.Liu and E.S.Hanff. Selected Data Set from Static and Rolling Experiments on a 65° Delta Wing at High Incidence. RTO-TR-26 AC/323(AVT)TP/19,383-405.
二级参考文献14
1[2]Degani D.Numerical investigation of the origin of vortex asymmetry[R].AIAA Paper 90-0593,1990.
2[3]Moskovitz C A,Hall R M,DeJarnette F R.Effects of nose bluntness,roughness and surface perturbations on the asymmetric flow past slender bodies at large angles of attack[R].AIAA Paper 89-2236CP,1989.
3[5]Levy Y,Hesselink L,Degani D.A systematic study of the correction between geometrical disturbances and flow asymmetries[R].AIAA Paper 95-0365,1995.
4[6]Murman S M.Geometric perturbations and asymmetric vortex shedding about slender pointed bodies[R].AIAA Paper 2000-4103,2000.
5[8]Hunt B L.Asymmetric vortex force and wake on slender bodies[R],AIAA Paper 82-1336,1982.
6[9]Keener E R,Chapman G T,Kruse R L.Effects of Mach number and afterbody length on onset of asymmetric forces on bodies at zero sideslip and high angles of attack[R].AIAA Paper 76-66,1976.
7[10]Keener E R,Chapman G T,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[R].NASA TM X-3437,1977.
8[12]Degani D,Schiff L B.Computation of turbulent supersonic flows around pointed bodies having crossflow separation[J].Journal of Computational Physics,1986,66(1): 173-196.
9[15]Dexter P C,Hunt B L.The effect of roll angle on the flow over a slender body of revolution at high angles of attack[R].AIAA Paper 81-0358,1981.