Optimization and performance analysis of a supersonic conical-flow waverider for a deck-launched intercept mission

Abstract

An aircraft configuration for a deck launched intercept mission was investigated. The mission requirements for the carrier-launched and recovered aircraft included Mach 6 cruise out to a 1000 nautical mile combat radius and 20 minutes of combat followed by return to the carrier. A conical-flow waverider served as the starting point for the aircraft configuration. A hydrocarbon scramjet was integrated with the waverider body. The aft end of the waverider was faired to decrease the base area thereby reducing the transonic base drag. A numerical optimization was then completed to maximize the product of L/D (lift to drag ratio) and I sub sp (specific impulse). Variables for the optimization included the cone shock angle (used to derive the conical flow waverider) and the geometry of both the waverider body and the integrated propulsion system. The vehicle was constrained to a minimum volume of 3240 cubic feet, a maximum span of 60 feet and a fixed length of 60 feet. The integrated propulsion system was constrained to produce a minimum contraction ratio of 12.0 and assurance that the cowl shock was within an acceptable distance of the inlet shoulder of the combustor. The optimum configuration met or exceeded all constraints. L/D comparisons were made between the integrated configuration (i.e., the subject of this study), pure Mach 6 optimized waveriders and historical trends.