"A large wind tunnel, approximately 8 feet in diameter, has been converted to transonic operation by means of slots in the boundary extending in the direction of flow. The usefulness of such a slotted wind tunnel, already known with respect to the reduction of the subsonic blockage interference and the production of continuously variable supersonic flows, has been augmented by devising a slot shape with which a supersonic test region with excellent flow quality could be produced. Experimental locations of detached shock waves ahead of axially symmetric bodies at low supersonic speeds in the slotted test section agreed satisfactorily with predictions obtained by use of existing approximate methods" (p. 1297).

Report presenting flight tests with an airplane equipped to vary the longitudinal-control-system dynamic characteristics over a wide range. Control is obtained through a stabilizer force-command position-feedback longitudinal-control system. Results at a Mach number of 0.80 at 35,000 feet altitude, Mach number of 0.35 at 5,000 feet altitude, and normal-acceleration response are provided.

"Static longitudinal and lateral stability characteristics of a swept-wing fighter-bomber airplane model with a top inlet have been determined experimentally. In addition, vertical-tail effectiveness, spoiler effectiveness, effects of several store configurations, and effects of mass flow were investigated. Tests were made at Mach numbers of 1.6, 1.8, 2.0, 2.2, and 2.35 and Reynolds numbers, based upon mean aerodynamic chord, of between 2.0x10(exp 6) and 2.5x10(exp 6)" (p. 1).

"A summary of the locations, extents, and intensities of turbulent areas encountered during a flight investigation of the jet stream is presented. The data were obtained from NACA VGH time-history records" (p. 1).

Report presenting heat-transfer measurements for a flat-face cylinder-flare configuration in free flight up to Mach number 2.7. Skin temperatures were measured at 12 points along the configuration. Information about the heating rates was compared to data obtained from theoretical calculations.

Report presenting wind-tunnel measurements of the forces and moments of a model of an airplane with pitch-up tendencies at angles of attack up to 70 degrees. The model had an unswept, low-aspect-ratio wing, a long fuselage, and a high horizontal tail. Results regarding longitudinal and lateral directional characteristics, effects of wing-tip tanks and tip-tank fins, and longitudinal characteristics of the fuselage-tail combination are provided.

Report presenting an investigation of several wingless missile configurations for a range of Mach numbers to determine their lift, drag, and pitching-moment coefficients. Results for missiles having nose controls and missiles having tail controls are provided. The results were also compared to a conventional missile with wings.

Report presenting a wind-tunnel investigation of several wingless missile configurations. Lift, drag, and pitching-moment coefficients were measured for a range of Mach numbers. Results regarding the missiles with nose controls and missiles with tail controls are provided.

Report presenting an investigation to determine some of the effects of lip geometry on drag and pressure recovery of a normal-shock nose inlet. Lip bluntness, lip camber, and forebody angle were all explored as possible variables. Total-pressure recoveries, external drags, duct total-pressure distributions, lip and forebody pressure distributions, and Schileren photographs are provided.

Report presenting an investigation to determine the effects of magnitude and circumferential extent of inlet total-pressure distortions on the overall an component performance of a current turbojet engine. Results regarding the pressure and temperature profiles, component performance, engine pumping characteristics, net thrust and net-thrust specific fuel consumption are provided.

Report presenting an investigation at Mach number 4.06 on a typical supersonic airplane model with a 40 degree sweptback wing. The purpose of the investigation was to determine the effectiveness of using wedges on the body and on the vertical tail to increase the static directional stability. Results regarding the longitudinal characteristics and lateral characteristics are provided.

Report discussing an investigation of the aerodynamic characteristics of a model of an escape capsule with and without stabilizing fins for a supersonic bomber-type airplane. Lift, drag, longitudinal and lateral stability characteristics, and photographs of the capsule model are presented.

Report presenting tests to determine the effects of sting-support interference on the zero-lift drag of two bodies of revolution (with and without boattailing). The sting support consisted of a constant-diameter sting followed by a sting flare terminating in a cylindrical support. Results regarding the effect of sting length and sting diameter are provided.

"The present investigation was conducted in the Langley high-speed 7-by 10-foot tunnel to determine the static longitudinal and lateral stability characteristics at high subsonic speeds of two canard airplane configurations previously tested at supersonic speeds. The Mach number range of this investigation extended from 0.60 to 0.94 and a maximum angle-of-attack range of -2deg to 24deg was obtained at the lowest test Mach number. Two wing plan forms of equal area were studied in the present tests; one was a 60deg delta wing and the other was a trapezoid wing having an aspect ratio of 3, taper ratio of 0.143, and an unswept 80-percent-chord line" (p. 1).

From Summary: "Presented herein are the results of a study of some of the problems associated with the cross-roll filter, command computer, and g-limiter of an automatic interceptor system."

Memorandum presenting an analysis of probable heat-exchanger weights for stationary and rotary regenerator heat exchangers for use in a hydrogen-expansion turbine engine. This is because rotary regenerators offer possibilities for a considerably lighter heat-exchanger core, possibly one-fourth that of the stationary regenerators.

Report presenting an analysis of probable heat-exchanger weights for stationary and rotary regenerator heat exchangers for use in a hydrogen-expansion turbine engine. Rotary regenerators may be used for a considerably lighter heat-exchanger core, possibly one-fourth that of the stationary regenerators.

Memorandum presenting a theoretical mixed-jet one-spool turbofan engine analyzed over a range of flight Mach numbers up to 2.95. The engine was characterized by an eight-stage fan-compressor unit. Results regarding performance maps, rotating stall, turbofan inlet axial velocity, and weight-flow variations are provided.

Memorandum presenting an experimental and analytical study made at transonic speeds up to Mach number 1.43 to determine the ability of present calculation procedures to predict transonic drag-rise changes which result from physical model changes. Both wing-body and wing-body-tail configurations were investigated.

Report presenting an experimental and analytical study at transonic speeds up to Mach number 1.43 to determine the ability of present calculation procedures to predict transonic drag-rise changes resulting from physical model changes. Results regarding wing-body configurations, wing-body-tail configurations, and drag-rise change are provided. With the exception of the model with the bluff forebody and afterbody, the currently available calculative procedures provided estimates of transonic drag within 15 percent of measured values.

Memorandum presenting a summary of ignition-lag data obtained from 1949 to 1956 in terms of dependence on temperature, pressure, reactor geometry, mixing method, and propellant composition. Analysis of the results and comparisons with data from other sources indicate agreement with a chemical kinetics model provided that mixing is reasonably energetic.

Report presenting a compilation of most of the zero-lift drag obtained from free-flight measurements on fin-stabilized bodies of revolution. Results regarding friction drag, base pressure and base drag, pressures on a forward facing step, and fin pressure drag are provided.

From Introduction: "The purpose of this report is to present the results of an analytical investigation of the engine characteristics of two-spool engines with high over-all compressor pressure ratio (12.0 at design). Some of the turbine design problems encountered in a single-spool engine with current compressor pressure ratio (7.32 at design) were investigated in reference 1. The investigation was extended in reference 2 to cover the effect of mode of engine operation on the turbine design requirements and engine performance for a single-spool engine with current compressor pressure ratio."

"Flat 2024-T3 aluminum panels measuring 11 inches by 13 inches were tested in the near noise fields of a 4-inch air jet and turbojet engine. The stresses which were developed in the panels are compared with those calculated by generalized harmonic analysis. The calculated and measured stresses were found to be in good agreement. In order to make the stress calculations, supplementary data relating to the transfer characteristics, damping, and static response of flat and curved panels under periodic loading are necessary and were determined experimentally. In addition, an appendix containing detailed data on the near pressure field of the turbojet engine is included" (p. 703).