Additional experiments with flat-top wing- body combinations at high supersonic speeds

s of f l a t - t o p wing-body combinatiois.I n general, t h e s e c o n f i g u r a t i o n s c o n s i s t of one h a l f of a body of r e v o l u t i o n mounted beneath a wing of e s s e n t i a l l y arrow p l a n form.A t t h e r o o t , t h e wing l e a d i n g edge coincides with t h e nose of t h e f u s e l a g e and t h e t r a i l i n g edge coirlcides with t h e f u s e l a g e base.V a r i a t i o n s i n model geometry st.udied include wing t r a i l i n g -e d g e sweep, t o e a d d i t i o n of a u x i l i a q bodies, downward d e f l e c t i o n of wing t l p s t c simulate v e r t i c a l fins, wing d i h e d r a l , wing leading-edge sweep, f u s e l a g e f i n e n e s s r a t i o , and f u s e l a s e p r o f i l e shape.pitching-momect c h a r a c t e r i s t l c s were cbtained a t Ylch numbers from 3.00 t o 6.28 and a n g l e s of a t t a c k up t o 4 ' .L i f t , drag, and Many of t h e c o n f i g u r a t i o n s t e s t e d were found t o be r e l a t i v e l y e f f i c i e n t .m a x i m u m l i f t -d r a g r a t i o s measured were greater than 6. maximum l i f t -d r a g r a t i o s measured were 7.2 a t M = 3.00 and M = 4.24, 6.6 a t M = 7.05, and 5.3 a t M = 6.28, although t h e s e values were not a l l For example, a t Mach numbers from 3 t o 5 , 60 p e r c e n t of t h eThe h i g h e s t obtained with t h e same configuration.I c NACA RM ~56111 b in conjunction with other practical considerations of hypersonic flight entirely beneath a wing of essentially arrow plan form.leading edge at the root coincided with the nose of the fuselage and the trailing edge coincided with the fuselage base.downward on some models, thereby simulating vertical fins.led to the study of configurations consisting of a fuselage situated IThe wing Wing tips were deflected It was estimated in reference 1 that sensibly complete aircraft of this flat-top design would develop lift-drag ratios in excess of 6 at a Mach number of 5.These estimates were, in the main, confirmed by preliminary experimental results and a maximum lift-drag ratio of 6.6 at a Mach number of 5 was obtained.By way of comparison, this value was 15 percent higher than the lift-drag ratio obtained for an entirely comparable symmetric model.The investigation made in reference 1 was, however, of rather limited scope.The only configuration shape variables studied were wing plan form and wing-tip-flap deflection.The experimental investigation begun in reference 1 has Seen extended to cover several additional shape variables including fuselage fineness ratio, fuselage profile shape, wing leading-edge sweep, and the addition of auxiliary bodies.investigations of wing plan form and tip-flap deflection have also been made.The effects of these variables on the aerodynamic characteristics of flat-top configurations have been determined at Mach numbers from 3.00 to 6.28.present report.Additional .?"ne results of these studies are the subject of the NOTATION