Investigation Of Aerodynamic Characteristics Of Projectile With WAF At Super High Speeds

With the continuous increase of modern vehicle's flight velocity, it has become the important study that of hypersonic aerodynamics and aerodynamic heating. The research on aerodynamic characteristics of wrap-around fin and wing-body combination was carried out at super high speeds in this dissertation. Three dimensional flow over wrap-around fin and wing-body combination and aerodynamic heating process were simulated numerically in super high speeds using FLUENT. Wind tunnel test of projectile with wrap-around fin at different roll angle was finished also.Mathematic model for investigating wrap-around fin's aerodynamic characteristics at super high speeds was established. The time-dependent compressible Reynolds average Navier-Stokes equations were used as governing equations. Second-order upwind scheme was adopted for the convective fluxes discretization. For numerical simulation of hypersonic flow, the AUSM+ scheme was introduced in order to reduce numerical dissipation and improve the resolution of shock discontinuities and computational accuracy. The Reynolds stress turbulent model was considered in this dissertation. The conformal mesh technology was applied in modeling mesh of wrap-around fin-body combination. It both satisfies the requirement of different zonal mesh density and viscous calculation, and decreases the amount of computational mesh.Three dimensional flow over wrap-around fin was simulated numerically at super high speeds with computational program and numeric scheme studied in this dissertation. Reasonable flowfield structure information and aerodynamic data were obtained by numerical simulation. Mechnism of producing lift of wrap-around fin at zero angle of attack was analyzed selectively. Change law of wrap-around fin's aerodynamic characteristics as a function of Mach number and angle of attack was investigated. The effects on aerodynamic performance of fin's leading edge nib angle and curvature were researched simultaneously.Numerical simulation of flow over wrap-around fin-body combination was done at super high speeds. The influences of inflow Mach number and angle of attack on wrap-around fin-body combination's flowfield and aerodynamic characteristics were studied in detail. Reasonable flow strcture and experimental data were obtained by wind tunnel test. Numerical result was almost in the same with experimental data. The wind tunnel test validates the correctness and reliability of the numerical calculation program studied in this dissertation.Computational model for studying the aerodynamic heating of wrap-around fin was built. Combinating the flow and structure governing equations which were relatively independent in form, aerodynamic heating process of wrap-around fin was solved at super high speeds using integration numerical simulation coupled flow, thermal and structure. Aerodynamic heating performance of wrap-around fin was achieved with different Mach number and angle of attack.Research work in this paper has an instructing meaning of investigating flight vehicle's aerodynamic characteristics with long ratio of slenderness in super speed. It supplys a foundation of wrap-around fin's basic research and engineering application design at the same time.The study method and result has guiding significance for investigating flight vehicle's aerodynamic characteristics with long ratio of slenderness at super high speeds. It provides the reference foundation for wrap-around fins' basic research and engineering application design.