FOR AERONAUTICS

Performnce characteristics of three similar canard-type, long-range ram-jet missiles were investigated to evaluate the relative merits of several types of engine installation. Force and engine pressure recovery characteristics of the individual missiles were obtained from previous investigations in the Lewis 8- by 6-foot supersonic wind tunnel at Mach nunhers from 1.5 to 2.0 for a range of angle of attack, control surface deflection angle, and engine mass-flow ratio. The engine instal-lations included (1) a twin-engine nacelle-type installation strut-munted above and below the fuselage in a vertical plane through the fuselage center line, (2) a twin-engine nacelle-type installation nmunted on the wing, and (3) a single-engine fuselage-contained installation with an underslung scoop-t~e inlet. Average Reynolds number based on the. mean aero@amic chord of the wing varied from about 6.9XL06 to 8.4x106. Results of the investigation indicated that the lift curve slopes of the three modeb were about the same and decreased with increasing Mach number. The lowest zero-lift drag was obtained with the underslun