Report discussing an investigation of the longitudinal stability, trim, and drag of a rocket-propelled model at low lift coefficients at a range of Mach numbers. the configuration included a wing and horizontal tail of aspect ratio 4 and thickness ratio in the streamwise direction of 6 percent.

Report presenting a preliminary investigation of a wedge-type compression surface mounted vertically in a circular cowling conducted in the supersonic wind tunnel at a Mach number of 1.90 and range of angles of attack. With symmetrical cowling, the pressure recovery and stability characteristics comparable to a conical inlet were obtained, but twin-duct flow interaction was observed. Results regarding the pressure recovery and stability characteristics and effects of removing the lower cowl lip and perforating the wedge centerbody are provided.

Report presenting an investigation of the effects of the wake resulting from control-surface deflection on the internal performance of two supersonic diffusers and on the engine-body interference drag in the 8- by 6-foot supersonic wind tunnel at Mach number 2.0. Results regarding the internal-flow evaluation, high-pressure-recovery diffuser, and drag evaluation are provided.

"An investigation was made of the performance of nine conical cooling-air ejectors at primary jet pressure ratios from 1 to 10, secondary pressure ratios to 4.0, and a temperature ratio of unity. This phase of the investigation was limited to conical ejectors having shroud exit to primary nozzle exit diameter ratios of 1.06 and 1.40, with several spacing ratios for each. The experimental results indicated that the pumping range and amount of cooling-air flow obtained with a 1.06 diameter ratio ejector were relatively small for cooling purposes but that the maximum possible thrust loss, which occurred with no secondary flow, was only 7 percent of convergent nozzle thrust" (p. 1).