From Introduction: "The purpose of this report is to present the results of the analysis and to compare them with the experimental results of the transonic turbine."

Memorandum presenting a rocket-propelled model of a representative 35 degree sweptback wing airplane design at high subsonic Mach numbers to investigate the possibility of the existence of coupled longitudinal and lateral motions. The data indicate the existence of sustained longitudinal motions of appreciable amplitude forced by lateral oscillations. The longitudinal motions had twice the frequency of the lateral oscillations and are shown to be the result of aerodynamic moments due to sideslip and inertial cross coupling.

"A considerable weight reduction in the turbine wheel of an aircraft gas turbine is attained through the use of high-aspect-ratio rotor blading. An experimental investigation was made to compare the performance of a turbine of conservative aerodynamic design having shrouded rotor blades with an aspect ratio of 4.48 with that obtained from both a shrouded and an unshrouded rotor design with aspect ratio of 2.24. The use of high-aspect-ratio rotor blades had a negligible effect on the turbine efficiency" (p. 1).

Report presenting an investigation to determine the blade torsional deflection of three supersonic-type propellers at various operating conditions. Blade-torsional deflection was found to produce appreciable results that can be predicted by theory with good accuracy. Results regarding the efficiency, thrust coefficient, and power coefficient are provided.

An investigation was conducted on a 35 deg swept-wing fighter airplane to determine the effects of several blunt-trailing-edge modifications to the wing and tail on the high-speed stability and control characteristics and tracking performance. The results indicated significant improvement in the pitch-up characteristics for the blunt-aileron configuration at Mach numbers around 0.90. As a result of increased effectiveness of the blunt-trailing-edge aileron, the roll-off, customarily experienced with the unmodified airplane in wings-level flight between Mach numbers of about 0.9 and 1.0 was eliminated, The results also indicated that the increased effectiveness of the blunt aileron more than offset the large associated aileron hinge moment, resulting in significant improvement in the rolling performance at Mach numbers between 0.85 and 1.0. It appeared from these results that the tracking performance with the blunt-aileron configuration in the pitch-up and buffeting flight region at high Mach numbers was considerably improved over that of the unmodified airplane; however, the tracking errors of 8 to 15 mils were definitely unsatisfactory. A drag increment of about O.OOl5 due to the blunt ailerons was noted at Mach numbers to about 0.85. The drag increment was 0 at Mach numbers above 0.90.

Results are presented of wind-tunnel investigations at Mach numbers of 0.60 to 0.94 and angles of attack of -2 degrees to about 24 degrees to determine the lateral control characteristics of spoilers with various wing chord-wise and spanwise locations and spoiler spans and deflections on thin 60 degree delta wing of NACA 65a003 airfoil section parallel to free stream.

Memorandum presenting an analysis to determine the compressor pressure ratios and specific weight flows obtainable with single-stage air-cooled turbines for both nonafterburning and afterburning turbojet engines operating at a flight Mach number of 2 in the stratosphere. Wide ranges in turbine-inlet temperature, tip speed, hub-tip radius ratio, and coolant-flow ratio were considered.

Report presenting an investigation of a conservatively designed experimental cold-air turbine with and without a shroud band on the rotor blades. The tip of the rotor blade was oriented toward the tangential direction so that the adverse effect of blade-tip scraping would not be appreciable. The efficiency for the unshrouded-rotor configuration was about one point higher than for the shrouded rotor.

Report presenting an investigation to study the aerodynamic problems associated with a turbine design for a mode of engine operation which utilizes turbine stator adjustment to maintain a fixed compressor operating point. An indication of the turbine requirements for a particular compressor operating point indicated that a feasible sing-stage air-cooled turbine design could be obtained within reasonable aerodynamic limits. Results regarding the performance of the turbine, pressure ratios, and operational requirements are provided.

Report presenting an investigation of combustion oscillations using white fuming nitric acid and a hydrocarbon fuel in a 1000-pound-thrust rocket engine. Results regarding rotary oscillation shown by 40,000-frame-per-second photographs, oscillations recorded by streak photography, ion gap traces, pressure measurements, and plastic chamber erosion are provided.

From Introduction: "This paper presents the results of an investigation conducted in the Langley 11-inch hypersonic tunnel to evaluate methods of increasing maximum lift-drag ratio."

Report presenting flight measurements of the buffeting characteristics of the Bell X-5 airplane at 58.7 degrees of sweepback at a range of Mach numbers and altitudes. Information about tail buffeting and wing buffeting at several angles of attack is provided. The pilot considered the buffeting to be unobjectionable throughout the entire test region.

Report presenting an investigation in the transonic tunnel to determine the basic aerodynamic and loading characteristics of an unswept-wing-fuselage combination with a wing of aspect ratio 4, taper ratio 0.5, and NACA 65A004 airfoil sections. Force, moment, and pressure measurements were obtained for a range of Mach numbers and angles of attack.

"Results are reported of current studies at the Forest Products Laboratory to develop a metal-bonding adhesive with greater resistance to temperatures up to 600 degrees Fahrenheit that is easier to use than present ones. Most promising is a formulation of phenol and epoxy resins modified with hexamethylenetetramine and supplied for use as a dry tape supported on a glass-mat base" (p. 1).

"A 1/10-scale rocket model of the Lockheed XF-104 with faired inlets has been flown over a Mach number range from 0.80 to 1.45 to determine low-lift drag and a limited amount of stability data. The center-of-gravity locations were 4.0 and 1.5 percent of the mean aerodynamic chord before and after sustainer firing, respectively. Oscillations induced by pulse rockets were used to determine stability data. The external transonic drag coefficient increased from a value of 0.0160 at Mach number 0.80 to a maximum of 0.0432 near Mach number 1-13, with a drag rise Mach number of about 0.93. At Mach numbers where it could be determined, the model exhibited stable dynamic and static stability characteristics at low lift" (p. 1).

Report presenting an investigation at high subsonic speeds of a complete model with one of four types of wings: a basic sweptback wing, an M-shaped wing, a W-shaped wing, and a cranked wing. All of the wings had the same aspect and taper ratio and were tested at the same range of Mach numbers. Results regarding longitudinal characteristics and lateral characteristics of the different wings are provided.

From Introduction: "In reference 1, in which the performance of conical supersonic scoop inlets on circular fuselages is reported, the drag of the bottom-inlet configuration was considerably higher than for the top inlet."

"The performance of liquid fluorine and liquid ammonia as a propellant combination was evaluated in 1000-pound-thrust rocket engines operated at a chamber pressure of 600 pounds per square inch absolute. Values of specific impulse, characteristic velocity, thrust coefficient, and heat rejection were obtained as functions of propellant mixture ratio for each of four injectors: a triplet, a showerhead, and two like-on-like types" (p. 1).

Memorandum presenting a study of the ignition of ammonia and mixed oxides of nitrogen at 160 degrees Fahrenheit made with and without fuel additives utilizing small-scale rocket engines of approximately 200 pounds thrust. All experiments were conducted at sea-level pressures except two at a range of pressure altitudes. Results regarding the use of lithium as a catalyst, calcium as a catalyst, and no apparent catalyst are provided.

Report presenting a study of four short annular diffusers with different diffuser passage area variations and with various combinations of straightening vanes, vortex generators, splitters, and boundary layer suction for flow control. Results regarding turbine discharge whirl, diffuser passage modification, and boundary layer control are provided.

Report presenting an experimental investigation to determine the effect of several wedge-type boundary-layer diverters on drag and inlet pressure recovery in the 8- by 6-foot supersonic wind tunnel at Mach numbers of 1.5, 1.8, and 2.0. The model consisted of two rectangular ramp-type inlets mounted on the NACA RM-10 body of revolution. Results regarding variation of inlet pressure recovery and configuration drag with inlet mass-flow ratio, changes in the shock pattern off the inlet ramp, pressure-recovery-mass-flow characteristics, and drag coefficients are provided.

Report presenting an exploratory investigation of three aluminum disoaps of C(sub 8) acids to determine the gelling properties and stabilizing ability in slurries of 50 percent magnesium power and JP-4 fuel. All of the soaps were found to gel the slurries satisfactorily and to exhibit adequate reproducibility of gel properties. Results regarding the soap behaviors, effects of temperature, viscosity, and formation of the gel structures are provided.

"An experimental investigation has been conducted to determine the dynamic stability and control characteristics in hovering and transition flight of a 0.13-scale flying model of the Convair XFY-1 vertically rising airplane with the lower vertical tail removed. The purpose of the tests was to obtain a general indication of the behavior of a vertically rising airplane of the same general type as the XFY-1 but without a lower vertical tail in order to simplify power-off belly landings in an emergency. The model was flown satisfactorily in hovering flight and in the transition from hovering to normal unstalled forward flight (angle of attack approximately 30deg)" (p. 1).

Report presenting an investigation of an experimental 15-stage axial-flow compressor to determine the effect of inlet-annulus area blockage on disrupting the rotating stall and altering the overall performance and stall characteristics of the compressor. It is part of a general investigation to determine how to alleviate the general problems of blade vibration and poor off-design performance associated with compressor rotating stall.