Aerodynamic Aspects of Future Space Vehicles and Implications for Testing.

A review of the technical characteristics and problems associated with a lifting spacecraft operating near the earth and in other planetary atmospheres. All phases of flight are considered. The major use of lifting spacecraft would appear to be for maneuvering in orbital flight, but only if rather large plane or heading changes and side range are needed. For moderate maneuvers, a ballistic spacecraft equipped with rocket propulsion may be more attractive in cost and availability. If maneuvering is important, powered propulsion will be required during exit and while in orbit, and could be useful during reentry in effectively increasing the lift-to-drag ratio or providing for power-on landings. A lifting spacecraft might provide more efficient performance than the ballistic craft if it were lightweight and had a high lift/drag ratio; however, cooling problems would be severe. Research is required on cooling methods and materials. Range and testing facility design presents difficult problems for a lifting reentry vehicle, or any vehicle at speeds of Mach 10 or 20. 20 pp. Ref.