From Introduction: "The purpose of this paper is to discuss and evaluate some of the input signals or control parameters which have been experimentally employed to operate turbojet inlet-control systems. These include the normal-shock position, the oblique-shock position, and the diffuser-exit Mach number. The discussion is based on results obtained at the NACA Lewis laboratory during control investigations of ram-jet engines (ref. 1 to 5) and during a study on the control of a supersonic inlet for the J34 turbojet engine (refs 6 and 7)."

Report discussing the aerodynamic loading characteristics of a 45 degree sweptback wing with leading-edge chord extensions, including the effects of a spoiler-slot-deflector aileron. The wing section loading, wing-panel loading, and chord-extension loading are described.

Report presenting an investigation of the influence of high-altitude supersonic flight on the operation and effectiveness of turbine-blade liquid-cooling systems for application in turbojet engines in guided missiles and in supersonic aircraft. The problems encountered in liquid-cooling systems were investigated with reference to several specific designs for alternate heat-rejection mediums.

"Tests of a 1/20-scale dynamically similar model of the Northrop B-35 airplane were made to study its ditching characteristics. The model was ditched in calm water at the Langley tank no. 2 monorail. Various landing attitudes, speeds,and conditions of damage were simulated during the investigation. The ditching characteristics were determined by visual observation and from motion-picture records and time-history acceleration records" (p. 1).

Report presenting the results of flight testing to determine the zero-lift drag of an NACA 65-009 airfoil at a specified aspect ratio. The results are compared to previous testing of unswept and swept-back arrangements. The swept-forward and swept-back airfoils were found to produce lower values of zero-drag lift than the unswept airfoil.

"The frequency of blade temperature to exhaust gas temperature is presented for two locations in the blade and at several operating conditions. The frequency response was determined by Fourier analysis of transient data. Two analytical methods are presented, and results are compared with experimental data. Dynamic response of turbine-blade temperature to exhaust-gas temperature exhibited the form of an approximate first-order lag" (p. 1).

Report presenting an investigation of the effects of rocket-armament-exhaust-gas ingestion on the performance of a supersonic-inlet J34-turbojet-engine installation at Mach 2. Rockets were fired from two different spike positions and with the engine at high or low speed. Results regarding engine air flow, temperature, and flame-out are provided.

Memorandum presenting an investigation of a 2:1 area-ratio diffuser of length equal to the inlet diameter with several arrangements of simple rectangular vortex generators over a speed range up to an inlet Mach number of 0.5. The investigation was for an inlet boundary layer of 5 percent of the inlet diameter, a condition for which this diffuser had substantial separated areas with no vortex generators. Results regarding the diffuser with no vortex generators, counterrotating vortex generators, other arrangements investigated, and a comparison with results from previous diffuser research are provided.

"During the flight program on the Bell X-5 airplane with 59 degrees sweepback to determine the practical Mach number and normal-force coefficient limits of this configuration, a reduction in static longitudinal stability was encountered in maneuvering flight. A determination of the boundary for reduction of longitudinal stability extending to a Mach number of 0.98 is presented in this paper. A reduction of static longitudinal stability existed for all elevator and all stabilizer-executed maneuvers" (p. 1).

Memorandum presenting two rocket-propelled models flight tested at Mach numbers from 0.8 to 1.5 to determine the effect of a fuselage indentation on the drag of a 52.5 degree sweptback-wing-body configuration with two large strut-mounted store symmetrically located above and below the fuselage. The fuselage had a symmetrical, Mach number 1.0 indentation designed to cancel the wing area normal to the plane of symmetry. Results regarding total drag and pressure drag are provided.

Report presenting an investigation of three pairs of 1/10-scale Republic F-105 airplane wings at subsonic to low supersonic speeds in free flight by utilizing rocket-propelled models to investigate the possibility of flutter. The wing plan form was swept back 45 degrees at the quarter-chord line and had an aspect ratio and taper ratio based on the exposed panels of 2.92 and 0.5, respectively. Testing did not show the existence of flutter for the full-scale wings in clean condition up to Mach number 1.47.

Report presenting the results of a limited research program initiated to study the effects of a hot propulsive jet on the longitudinal stability characteristics of a fighter-type airplane configuration. The data was obtained from a rocket-boosted free-flight model investigation over a range of Mach numbers using four models that differed only in the position and size of the horizontal tail. Results regarding the time histories, trim, normal force, pitching moment, aerodynamic-center location, dynamic stability, trim drag, and pressure data are provided.

Friction and surface damage of several materials that are resistant to corrosion due to liquid metals was studied in air. The values of kinetic friction coefficient at low sliding velocities and photomicrographs of surface damage were obtained. Appreciable surface damage was evident for all materials tested. The friction coefficients for the combinations of steel, stainless steel, and monel sliding against steel, stainless steel, nickel, Iconel, and Nichrome ranged from 0.55 for the monel-Inconel combination to 0.97 for the stainless-steel-nickel combination; for steel, stainless steel, monel, and tungsten carbide against zirconium, the friction coefficient was approximately 0.47.

Memorandum presenting a correlation of analyses of the effect of distributed surface injection on the heat transfer and skin friction associated with the turbulent boundary layer at high speeds to eliminate the effects of Mach and Reynolds number. Data for heat transfer and skin friction at three Mach numbers are compared with the analyses and the agreement is good.

Report presenting an experimental investigation in the transonic blowdown tunnel to determine effects of center-of-gravity location on the transonic flutter characteristics of a 45 degree sweptback-wing plan form of aspect ratio 4.0 and taper ratio 0.6. Solid-construction models with streamwise NACA 65A004 airfoil sections and center-of-gravity locations at three different chords were fluttered at a range of Mach numbers.

Report presenting an analysis of the injection of water into the jet-engine exhaust in order to suppress noise during static ground operation of jet engines. The investigation is conducted with a simple rig which pumps high-pressure water into the exhaust of an afterburning jet engine. Results regarding the overall sound-pressure levels and frequency spectra of the noise are provided.

Report presenting an investigation of some of the factors that affect autopilot systems in airplanes.

Report presenting an investigation to determine the temperature and pressure distributions in the jets issuing from two parallel nozzles of a turbojet engine located close together and impinging on the ground at an angle of 20 degrees. Results regarding the jet-nozzle pressure ratio, constant-temperature parameters, and temperature contours are provided.

Memorandum presenting tests of a triangular-wing-airplane model equipped with high-lift devices and lateral and directional controls. The model consisted of an aspect ratio 4 triangular wing in combination with a fuselage of fineness ratio 12.5, a thin, triangular, vertical tail with a constant-chord rudder, and a thin, unswept, all-movable horizontal tail. Results regarding the effects of flap deflection and tail incidence on the pitching moment characteristics, lift and drag characteristics, and rudder effects are provided.

Theoretical performance for mixture of 36.3 percent liquid ammonia and 63.7 percent hydrazine with liquid oxygen bifluoride as rocket propellant was calculated on assumption of equilibrium composition during expansion for a wide range of fuel-oxidant and expansios ratios. Parameters included were specific impulse, combustion-chamber temperature, nozzle exit temperature, composition mean molecular weight, characteristic velocity, coefficient of thrust and ratio of nozzle-exit area to throat area. For chamber pressure of 300 pounds per square inch absolute and expansion to 1 atmosphere, maximum specific impulse was 295.8 pound-seconds per pound. Five percent by weight of water in the hydrazine lowered specific impulse from about one to three units over a wide range of weight-percent fuel.

Memorandum presenting an investigation of the effect of a 60 degree sweptback horizontal tail at two vertical locations on the static longitudinal stability of two 60 degree sweptback wing-body configurations with aspect ratios of 2.67 and 4.00 in the 8-foot transonic pressure tunnel. Tests were made at Mach numbers from 0.80 to 1.18 for angles of attack from -3 degrees to about 15 degrees.