Memorandum presenting a theoretical analysis of the supersonic flow about two-dimensional and three-dimensional axially symmetric models restricted by theoretical walls capable of removing the nose shock. Results regarding the supersonic-tunnel interference due to nonreflecting walls and supersonic-tunnel interference due to porous walls are provided.

Memorandum presenting results of a supersonic flutter investigation of three low-aspect-ratio control surfaces. Two controls were all-movable but the third had a fixed cutout. Results regarding the experiments and calculations are provided.

Memorandum presenting force-oscillation tests made in the 8-foot transonic pressure tunnel to investigate some effects of an overhang-type aerodynamic balance and of a flow spoiler on the dynamic hinge-moment characteristics of a full-span flap-type rudder on a 5-percent-thick, swept vertical fin of low aspect ratio. Test results how that the aerodynamic damping moment on the plain rudder becomes unstable near a Mach number of 0.975 and remains unstable to the maximum speed of the tests.

Report presenting performance of a two-dimensional external-compression inlet designed for various methods of inlet-engine matching up to Mach 3 at Mach 1.89 and Mach 0. Results regarding shock geometry, two-shock ramps, isentropic ramps, profiles, and cowl drag for the various Mach number tests are provided.

Memorandum presenting an investigation of hemispherical nose shapes of titanium, stainless steel coated with aluminum oxide, and uncoated stainless steel with lithium hydride and magnesium as internal coolants. Results regarding titanium models, stainless-steel models (uncoated), stainless-steel models coated with aluminum oxide, solution effects on the decomposition temperature of lithium hydride, effect of lithium hydride and magnesium on temperature measurements, and efficiency of models cooled with lithium hydride are provided.

Transonic flutter derivatives for unswept wing control surface configurations determined by pressure cell measurements. The control surfaces were mounted on a wing with an aspect ratio of 3, a taper ratio of 0.6, and a wing-thickness ratio of 0.06. Results regarding aerodynamic balance, vortex generators, splitter-plate configurations, and wedges are provided.

"A study has been made of a flare-cylinder configuration to investigate its feasibility as a reentry body of an intermediate range ballistic missile. Factors considered were heating, weight, stability, and impact velocity. A series of trajectories covering the possible range of weight-drag ratios were computed for simple truncated nose shapes of varying pointedness, and hence varying weight-drag ratios" (p. 1).

Report presenting an investigation at Mach numbers of 1.61 and 2.01 to determine the pressure distributions for a series of 20 controls on a 60 degree delta wing. Tests occurred at a range of angles of attack and control deflections. Results regarding basic pressure distributions, comparison of experimental and theoretical results, and experimental comparisons are provided.

Memorandum presenting an experimental investigation of the pressure-recovery performance of a fixed-geometry, two-cone, two-drag inlet at Mach number 2.95. Low drag was achieved by use of an internally cylindrical cowl with rapid flow turning that was within 4 degrees of the wedge angle for shock detachment. Results regarding the inlet performance and evaluation of inlet performance are provided.

Memorandum presenting results of tests for possible flutter of a dynamically and elastically scaled model of a proposed all-movable horizontal tail surface for the North American X-15 airplane. Tests at Mach number 6.86 were made on the scaled model and on several other configurations with lower stiffnesses.

Low cowl drag, external compression inlet with subsonic dump diffuser for high Mach number application.

Memorandum presenting an investigation conducted in the 10- by 10-foot supersonic wind tunnel to evaluate the performance of a shrouded injector burner with perforated domes employed in a 28-inch ramjet using gaseous hydrogen as fuel. Steady-state data were obtained at a pressure altitude of 77,000 feet and zero angle of attack. Results of the investigation showed that burning could be initiated under severe distortion conditions and that satisfactory combustor operation was accomplished up to a pressure altitude of 110,000 feet with no adverse effect on combustion efficiency.

Memorandum presenting a study of an acceleration-limiting control on a turbojet engine in order to determine its feasibility as an acceleration control. A proportional-plus-integral type of controller was used in the investigation. Results regarding the one-loop control and two-loop control are provided.

Memorandum presenting lift and drag characteristics that have been determined in flight in the landing-approach configuration on 41 jet-propelled fighter-type airplane arrangements, including various wing boundary-layer-control installations. Minimum comfortable approach speeds for carrier-type landings were evaluated for these airplanes by four test pilots. Results regarding the presentation of data, methods for the prediction of minimum comfortable approach speed, reasons for limiting approach speed, comparison of flight and predicted approach speeds, and comparison of test pilots' and service pilots' approach speed are provided.

Memorandum presenting an investigation conducted to measure and compare the total-pressure recovery and distortion characteristics at the compressor face of two single-place fighter-type airplanes with similar two-spool turbojet engines, but with dissimilar inlets. The total-pressure recovery was relatively independent of angle of attack and mass-flow ratio for both airplanes except for a significant decrease in pressure recovery with angle of attack for airplane B at the highest Mach numbers tested.

Report presenting lift and drag characteristics in the landing-approach configuration on 41 jet-propelled fighter-type airplane arrangements using flight testing. Minimum comfortable approach speeds were evaluated by four test pilots. Suggestions for achieving optimal speeds for approach under various conditions are also provided.

Report presenting an investigation to determine the longitudinal characteristics of an airplane model with a thin, highly swept and tapered wing of low aspect ratio equipped with plain leading-edge flaps in conjunction with blowing-type boundary-layer control applied to flap radius. Several leading-edge configurations and boundary-layer control system variables were also investigated.

Report presenting an investigation of a zero-cowl-drag, all-external-compression inlet with an abrupt area discontinuity or subsonic dump diffuser for high Mach number application. Results regarding the diffuser performance characteristics, effect of spike retraction, a comparison with other inlets, and some theoretical calculations related to the results are provided.

Memorandum presenting theoretical rocket performance for both equilibrium and frozen composition during expansion, which was calculated for the propellant combination of liquid ammonia with liquid oxygen at two chamber pressures and a wide range of pressure ratios and oxidant-fuel ratios. Some of the performance parameters explored include specific impulse, specific impulse in vacuum, combustion-chamber temperature, nozzle-exit temperature, molecular weight, molecular-weight derivatives, characteristic velocity, coefficient of thrust, ratio of nozzle-exit area to throat area, specific heat at constant pressure, isentropic exponent, viscosity, thermal conductivity, Mach number, and equilibrium gas compositions.

Report presenting an investigation in an altitude test chamber using a turbojet engine equipped with an afterburner and ejector to compare directly two techniques of determining thrust that are both applicable to flight installations. One method uses a swinging uncooled rake at the ejector outlet while the other requires extensive instrumentation to measure the momentum forces of systems and the force on the internal surface of the ejector nozzle. Results regarding the swinging-rake technique and internal-pressure technique are provided.

Report presenting an investigation to measure and to compare the total-pressure recovery and distortion characteristics at the compressor face of two single-place fighter-type airplanes with similar two-spool turbo-jet engines, but with dissimilar inlets. Results regarding compressor-face total-pressure surveys and surges encountered are provided.

Small metal spheres of various densities were fired at high speed into thick targets of copper and lead. In general, it was found that all of the penetrations could be correlated quite well for engineering purposes by a function relating the depth of penetration to the impact momentum per unit volume.

Report discussing the use of hot-wire anemometers to measure circumferential traces of specific-mass-flow variation for various radial positions at the rotor exit. Results regarding the rotor blade-wake traces, relative total-pressure ratio, and centrifuging of low-momentum fluid are provided.

Memorandum presenting an experimental investigation to determine the effect on drag of applying the moment-of-area-rule modifications to wing-body combinations with various wing plan forms. The effect of mounting air-to-air type missiles on the wing-mounted bodies of revolution which are part of the moment-of-area-rule modification was also investigated.