Memorandum presenting the effectiveness of chromium and aluminum as inhibitors for mass transfer and corrosion in nickel and nickel alloys by sodium hydroxide under free convection and at fluid velocities of 15 feet per second. The addition of 1 percent by weight of 325-mesh chromium powder to the caustic essentially eliminated the transfer for 50 hours at 1500 degrees Fahrenheit with a temperature difference of 20 degrees Fahrenheit and a flow of 15 feet per second. Results regarding the static test, the toroid test, and a description of the chemical reactions are provided.

Report presenting an investigation in the 16-foot and 8-foot transonic tunnel to determine the effects of Reynolds number and on a swept wing with camber. The wing had 45 degrees sweepback of the quarter-chord line, an aspect ratio of 4, a taper ratio of 0.6, and NACA 65A006 airfoil sections parallel to the plane of symmetry. Results regarding the effect of Reynolds number on the aerodynamic characteristics and effects of roughness strips are provided.

"During flight tests of two high-speed airplane configurations, violent cross-coupled lateral and longitudinal motions were encountered following abrupt rudder-fixed aileron rolls. The speeds involved ranged from a Mach number of 0.7 to 1.05. The motions were characterized by extreme variations in angles of attack and sideslip which resulted in load factors as large as 6.7g (negative) and 7g (positive) normal acceleration and 2g transverse acceleration" (p. 1).

Memorandum presenting an investigation of the landing characteristics of the X-1, X-3, and D-558-I straight-wing, the X-4, X-5, and D-558-II swept-wing, and the XF-92A delta-wing high-speed research airplanes. Results regarding normal landings, vertical velocities at ground contact, ground effect, and effects of lift-drag ratio are provided.

Memorandum presenting the results of flight testing of four different ski-equipped airplanes. Two types of skis were tested: hydro-skis designed to operate under or on the water surface and general-purpose skis designed to operate on a variety of surfaces but not underwater. A breakdown of the ski performance for each plane and ski combination is provided.

Report presenting the results of an investigation of the vibratory stresses of a dual-rotating propeller with both six-blade and eight-blade configurations using the NACA 6,000-horsepower propeller dynamometer. Attention was focused on the measurement of vibratory stresses caused by mutual blade interference of the front- and rear-propeller components. A range of blade angles and rotational speeds were used in testing.

Report presenting an investigation of a model of the Chance Vought XF8U-1 airplane to determine the effect of spin-recovery rockets on the recovery characteristics of the model. The investigation also included tests to determine the effect of simulated engine thrust on the recovery characteristics of the model. Results regarding yaw rockets, thrust-simulation rocket, and roll rockets are provided.

"An investigation of the endurance characteristics, at high Mach number, of the J65-W-7 engine was made in an altitude chamber at the Lewis laboratory. The investigation was made to determine whether this engine can be operated at flight conditions of Mach 2 at 35,000-feet altitude (inlet temperature, 250 F) as a limited-service-life engine. Failure of the seventh-stage aluminum compressor blades occurred in both engines tested and was attributed to insufficient strength of the blade fastenings at the elevated temperatures" (p. 1).

"Results are presented of a free-flight investigation between Mach numbers of 0.7 to 1.3 and Reynolds numbers of 3.1 x 10(exp 6) to 7.0 x 10(exp 6) to determine the longitudinal aerodynamic characteristics of the Northrop MX-775A missile. This missile has a wing, body, and vertical tail, but has no horizontal tail. The basic wing plan form has an aspect ratio of 5.5, 45 deg of sweepback of the 0.406 streamwise chord line, and a taper ratio of 0.4" (p. 1).

Memorandum presenting results of a free-flight investigation over a range of Mach and Reynolds numbers to determine the longitudinal aerodynamic characteristics of the Northrop MX-775A missile. The missile has a wing, body, and vertical tail, but has no horizontal tail. Results regarding basic data, drag, trim, lift and static stability, damping, and static pressure are provided.

Report presenting an investigation of a rocket-propelled model of the Douglas X-3 airplane in order to determine the lateral stability characteristics at zero angle of attack and to evaluate test and analysis technique. Results regarding time histories, lateral trim characteristics, general characteristics of lateral oscillation, and lateral stability derivatives are provided.

Report presenting an investigation to determine the static longitudinal and lateral stability characteristics of an airplane configuration with a trapezoidal wing with modified hexagonal airfoil section and a cruciform tail with 5 degree semiangle wedge section. Data were obtained at a range of angles of attack and sideslip.

Report presenting an investigation to determine the effects on internal performance of several geometric variables intended to produce a short, high-performance convergent-divergent nozzle. Some of the characteristics investigated included variations in the throat-contour radius, combinations of the shape of the convergent section and throat-contour radius, divergence angle, and shape of the divergent section.

Report presenting ignition-delay determinations of furfuryl alcohol and mixed butyl mercaptans with various white fuming nitric acids were made at several temperatures with a modified open-cup apparatus and a small-scale rocket engine of approximately 30-pounds thrust.

"An investigation of the low-speed, power-off stability and control characteristics of a 1/10-scale model simulating the Convair F-102A airplane has been made in the Langley free-flight tunnel. The model in its basic configuration and with two modifications involving leading- edge slats and an increase in vertical-tail size was flown through a lift-coefficient range from 0.7 to the stall. Only relatively low-altitude conditions were simulated" (p. 1).

From Summary: "The exhaust of a 6-inch-diameter ram-jet engine mounted in the Lewis 1- by 1-foot, Mach 3.1 supersonic tunnel was scavenged successfully with a 6.6-inch-diameter scoop. Limiting values of exhaust-to-stream static-pressure ratios and scavenge-system total-pressure ratios were determined for complete scavenging of the products of combustion. The scavenge-system operation influenced the engine exhaust-nozzle pressures under conditions of unstable scavenge flow."

Report presenting an investigation at Mach numbers 1.9 and 3.0 to demonstrate that a central core of air of high stagnation temperature can be produced in the test section of a supersonic wind tunnel. This makes performing wind tunnel testing cheaper and controls for more variables. Results regarding the core studies at Mach number 1.9 and 3.0 and diffuser performance at Mach number 1.9 are provided.

Report presenting an investigation performed at Mach number 2.96 to study the effects of some internal boundary-layer-control systems on the pressure recovery and stability characteristics of a side inlet with half a double-shock external compression surface. Counterbody bleed did not appreciably improve the performance of the inlet, and the maximum pressure recovery obtained was 62 percent. Results regarding the inlet performance with internal bleed and inlet performance with flow injection on external compression surface are provided.

Report presenting an experimental investigation of a series of fixed-geometry exhaust nozzles which simulated a variable exit, which was conducted in the 8- by 6-foot supersonic wind tunnel at Mach numbers 0, 0.6, 1.5, 1.7, and 2.0. Gross thrust performance of the long-shroud exit configurations was considerably better than the short-shroud. Results regarding flow coefficients, thrust characteristics, flight performance analysis of data, and shroud drag are provided.

From Introduction: "Data on the extent of decomposition of a sample of aluminum borohy-dride during long-term storage are presented."

Report presenting the effect of small variations in the axial position of the liner with respect to the nozzle on limiting rates of change of fuel flow and steady-state combustion efficiencies in a single tubular combustor. Data were obtained with two liner configurations at three combustor-inlet conditions. Results regarding transient combustion performance and steady-state combustion performance are provided.

From Summary: "An investigation was made to evaluate several design variations of hollow turbine blades intended for missile-engine use. In one general type, the airfoils were formed from sheet metal; in a second type, the blades were cast. The blades were operated in J47 engine at 7950 rpm turbine speed and 1260 degrees Fahrenheit tail-pipe temperature until a failure occurred or a service life of 30 hours had been attained."

Report presenting an investigation of an inlet mounted on the side of a fuselage and utilizing a horizontally oriented 14 degree ramp located at the top of the inlet at a variety of Mach numbers. The characteristics of this inlet were compared to a conventional ramp-type side inlet. Results regarding the pressure recovery and model drag coefficients, spillage drag coefficients, and thrust minus drag comparison are provided.

Report presenting an examination of the most promising air-cooled turbine blades for conventional turbojet engines, which are convection-cooled corrugated-insert and strut-supported blades. Successful analytical methods of predicting blade temperatures have been found for both blades. Results regarding turbine-engine performance, turboprop-engine performance, performance variations with compressor-discharge air bleed, and some cooling methods are provided.