One-Dimensional, Steady Flow with Mass Addition and the Effect of Combustion Chamber Flow on Rocket Thrust with a Supplement on the Integration of the Burning Equation

An algebraic so lu t ion is p r e s e n t e d to t h e p r o b l e m of o n e d imens iona l , s t e a d y s t a t e , a d i a b a t i c flow of a perfect gas in a cons t an t a rea c h a n n e l w i t h m a s s a d d i t i o n a t c o n s t a n t en tha lpy , c o n s t a n t r a t i o of specific h e a t s a n d m o l e c u l a r weight and negligible k i n e t i c energy , u s ing a d imens ion less q u a n t i t y p ropo r t i ona l t o t h e m a s s flux as a n i n d e p e n d e n t variable. P roper t i es of t h e so lu t ion a re descr ibed, a n d t h e coupled p rob l ems of m a s s a d d i t i o n m e c h a n i s m a n d a d j u s t m e n t of t h e flow to exter ior p re s su re a re discussed for t h e case of t h e solid p r o p e l l a n t rocke t m o t o r .