| Dynamic manipulation of forebody vortices as a means to obtain directional control of high-perfomance aircraft at high angles of attack is investigated. A tangent ogive shape of a slender body of the revolution is chosen as most representative of a real nose geometry of either a missile or military aircraft.In order to determine the characteristics of forebody flow asymmetry, a systematic study of lee-ward flow field over a slender body of the revolution on the high-angle-of-attack is conducted now.Effects of continuum, smooth, boundary-fitted and orthogonal grids on numerical results are discussed. And the generational method of 2-D grids is elucidated. The three dimensional Navier-Stokes equations are discretized using finite volume method, and time marching method is upwind scheme. The managements of boundary conditions and some industrial turbulence models are discussed.With the numerical method, investigations of the behaviors of the flow over the slender cylindrical body on the high-angle-of-attack are conducted, and the effects of the manual disturbances, the Mach number and the angle of attack on the flow field are discussed. The asymmetric vortex structure of the slender cylindrical body growing gradually along the symmetry axis of the slender body is shown.The SHM(Single Hole Microblowing) as a new perturbation active control technique was applied to the slender body with different Reynolds numbers at high angle of attack. With the analyzing and contrasting the distribution of the surface pressure distributions and the section side forces,the results indicated that the control ability of SHM has strong adaptability to various slender body at high angles of attack,and its control ability is effected by the Reynolds numbers.The investigation of the flow field show that the SHM control technique make an efficient control of side-force for both laminar and turbulent flow separation around forebody, and contribute to the research in the future. |
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