Report presenting a brief experimental investigation of a method for designing fuselage side air inlets with high internal total-pressure recovery and zero spillage drag at a specified design inlet mass-flow ratio. With a scoop designed according to the concept, near-zero spillage drag can be attained at the design inlet mass-flow ratio through a range of Mach numbers. Results regarding pressure recovery and drag due to the scoop are provided.

"For a period of ten to fifteen years intensive research and development has been conducted on turbojet propulsion systems for aircraft. During this period much has been learned about the system both from the standpoint of current usage and of future development possibilities. It is the purpose of this report to discuss the current status of the turbojet engine as produced in the United States and to discuss the future possibilities for improvement in the engine and in the fuel. The engine and fuel improvements will be evaluated both from the standpoint of probability of success in obtaining these improvements and from the standpoint of the effects of these improvements on the airplane performance" (p. 1).

Four 0.01643-scale equivalent-body-of-revolution models, designed to aid in the evaluation of the relative merits of various degrees of redesign of the existing (1955) Convair F-102 airplane, were launched from the helium gun at Wallops Island, Va., to determine their zero-lift drag at Mach numbers from 0.8 to 1.3. The data are presented with only sufficient analysis to validate their general subsonic level. Estimated values of the friction drag are presented at all Mach numbers to allow a comparison of the pressure drag values alone.