Three-dimensional Flow Past Blunt Bodies Research Articles

Investigation of hypersonic three-dimensional flow past blunt bodies within the framework of the parabolized Navier-Stokes equations

The flow of a homogeneous gas in a three-dimensional hypersonic viscous shock layer, which includes the shock wave structure, is examined within the framework of the parabolic approximation of the Navier-Stokes equations. The Navier-Stokes equations are simplified on the basis of the asymptotic analysis carried out in [1], are written in variables of the Dorodnitsyn type [2] and are solved by the method proposed in [3, 4] extended to the case of three-dimensional flows. The flow at zero angle of attack past elliptic paraboloids, two-sheeted hyperboloids and triaxial ellipsoids is calculated. Some results of investigating the flow past such bodies are presented. Flow past a sphere in the analogous approximation was considered in [5], where a comparison was also made with the solution of the complete Navier-Stokes equations [6, 7].

A numerical method of computing the three-dimensional flow past blunt bodies with a detached shock wave

A numerical method of computing the three-dimensional flow past blunt bodies with a detached shock wave

Calculation of three-dimensional flow past blunt bodies by the method of characteristics with account for equilibrium physicochemical changes

The p rob lem of hypersonic flow about blunt bodies is considered at an angle of a t t ack . For the n u m e r i c a l solut ion we use the method of [1] wi th sl ight changes . We se lec t new independent var iab les which are more conven ien t for c a l cu l a t i ng the flow about bodies of revo lu t ion of an angle of a t t ack . As the unknowns we consider the pressure and en tha lpy , which s impl i f ies the approx ima t ion of the state equa t ion wi th account for the p h y s i c o e h e m i c a l changes. w presents the de ta i l ed compu ta t i o n a l formulas. w describes the c o m p u t a t i o n a l s cheme for spher ica l ly b lunted cones at an angle of a t t ack . w presents some results of ca lcu la t ions of hypersonic flow about spher ica l ly blunted cones wi th h a l f a n g l e 0 w = 0 ~ 9~ ' a t the angles of a t t a ck c~ = 0, 5 ~ 10 ~ in per fec t (M=~ = ~) and eqn i l ib r inm dissoc ia t ing air . In par t icu la r , results are shown which i l lus t ra te the t i m e of shock appearance on the lee side of a blunt cy l inder at an angle of a t t ack . It is shown in w tha t i t is possible to se lec t spec i a l s imi la r i ty var iables , analogous to the corresponding var iab les in the case of a x i s y m m e t r i c flow, in which the pressure dis t r ibut ion along the g e n era t r ices of a cone with h a l f a n g l e 0 w > a differs on ly by 10%, both wi th respect to the m e r i d i o n a l angles ~ and with respect to the hypersonic flow condit ions. The resul t ing un iversa l curve may be used also for the approx ima te c a l c u l a t i o n of the pressure on the cone at an angle of a t t ack . w We refer the components of the ve loc i ty vector V to the v e l o c i ty V~, and the densi ty p to the f rees t ream densi ty p~, the pressure p and the enthaipy i are referred r e spec t ive ly to the quant i t ies p~ Vz~ and Vz~. We shal l seek the ve loc i ty vector in the cy l ind r i ca l coordina te system x, r, r (Fig. 1) in the form