A method for estimating the components of lift of wing-body combinations at supersonic speeds

The lift of wing-body combinations a t supersonic speeds i s obtained by means of an approximate linearized-theory a n a l y s i s which involves an assumption concerning t h e geometry of t h e body.Rectangular and triangular wing plan forms a r e t r e a t e d ; t h e wing and body may be a t d i ff e r e n t angles of a t t a c k .Also, the body may end a t t h e wing -t r a i l i n g edge o r may extend f a r t h e r back.The r e s u l t s a r e given i n t h e form of simple generalized curves from which t h e l i f t o f any s p e c i f i c configur a t i o n is r e a d i l y obtained. A comparison with s e v e r a l groups of experimental d a t a is presented t o show t h a t t h e method p r e d i c t s , with acceptable accuracy, t h e l i f t on t h e wing and on t h e body.A question proposed by F e r r a r i concerning t h e optimum wing incidence f o r minimum t o t a l drag i s investigated; it appears t h a t , a t moderate o r high supersonic speeds, wing incidence is of l i t t l e value i n reducing t h e t o t a l drag.