Fully Conservative Numerical Solutions for Unsteady Irrotational Transonic Flow About Airfoils

t i m e-a c c u r a t e s o l u t i o n s f o r s e v e r a l c a s e s are cam-pared with t h e r e s u l t s o f o t h e r unsteady t r a n-s o n i c codes. Good c o r r e l a t i o n i s shown w i t h re-s u l t s produced by t h e more e x a c t b u t computa-t i o n a l l y slower Euler-equations codes. Shock l o c a t i o n i s demonstrated t o b e b e t t e r p r e d i c t e d t h a n by s m a l l-p e r t u r b a t i o n o r q u a s i-c o n s e r v a t i v e schemes. s t a g n a t i o n enthalpy i d e n t i t y m a t r i x l o c a l Mach number