Shock Wave and Flow Field Development in Hypersonic Re-Entry
1961; American Institute of Aeronautics and Astronautics; Volume: 31; Issue: 2 Linguagem: Inglês
10.2514/8.5423
ISSN1936-9972
Autores Tópico(s)Plasma and Flow Control in Aerodynamics
ResumoA s t u d y is m a d e of w h e n a n d how a shock wave a n d c o n t i n u u m t y p e flow field develop in t h e nose region of a h igh ly cooled b l u n t body r e e n t e r i n g t h e a t m o s p h e r e a t hype r son ic speed a n d in a free m o l e c u l a r flow r e g i m e . T h e var ious types of flow reg imes e n c o u n t e r e d down to low a l t i t u d e cond i t i ons a re de l inea t ed , a n d t h e n a t u r e of t h e flow field a n d behavior of s o m e of t h e a e r o d y n a m i c cha rac t e r i s t i c s a re d iscussed . I t is shown t h a t for a h igh ly cooled body, free mo lecu l e flow cond i t i o n s occur a t a h i g h e r a l t i t u d e t h a n previously i nd i ca t ed . Based o n avai lable evidence, i t is sug ges ted t h a t k i n e t i c t heo ry so lu t ions , w h i c h a re essent ia l ly modified free mo lecu l e r e su l t s , a long w i t h t h e Navie r -S tokes e q u a t i o n s w i t h no surface sl ip, serve to define all of t h e flow reg imes except for a i a r row t r a n s i t i o n a l layer r e g i m e wh ich h a s a h e i g h t of less t h a n one factor of 10 in free s t r e a m dens i t y c h a n g e . I t is also sugges ted t h a t t h e a p p e a r a n c e of a definable shock wave occurs very ra icily in t e r m s of dens i ty c h a n g e n e a r t h e b e g i n n i n g of t h e t r ans i t i ona l layer r eg ime , a n d t h a t i t s locati•>:•, as in c o n t i n u u m flow, is governed pr incipal ly by t h e body geomet ry , whereas i ts t h i ckness is d e t e r m i n e d by a local m e a n free p a t h .
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