Report presenting studies of the final attack phase of an automatically controlled interceptor in flight and electronic simulators to investigate various airplane command and stabilization networks and to develop simple but adequate simulation techniques for the synthesis of automatic control systems. Results regarding automatic control with a simple command system, automatic control with the improved command system, and evaluation of the automatic control system in typical final attack maneuvers are provided.

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.

Report presenting one-tenth-scale models of two inlet configurations of fighter-type aircraft have been tested in the 4- by 4-foot supersonic pressure tunnel. The pressure-recovery and force characteristics of the inlets were determined as a function of mass-flow ratio, angle of inlet compression, angle of attack, and Mach number.

Report presenting an experimental investigation to assess the effects of sweep and taper ratio on the longitudinal characteristics of a wing-body combination at a range of Mach numbers. The results indicated that increased leading-edge sweep caused a progressive decrease in lift-curve slope and the variation of Mach number of the lift-curve slope and static longitudinal stability. Results regarding the effect of sweep, effect of taper ratio, and comparison with results of a previous investigation are provided.

Report presenting an investigation of the overall performance of a modified eight-stage axial-flow compressor as part of the investigation of the problems encountered in a high-pressure-ratio axial-flow compressor with transonic inlet stages. The maximum total pressure ratio obtained at design speed was 11.0 at an equivalent weight flow of 70.9 pounds per second with an adiabatic efficiency of 0.81. Results regarding modified compressor performance and comparison with predicted performance are provided.

Report presenting measurements of boiling burn-out heat flux for water flowing upward through an electrically heated tube for ranges of velocity, pressure, length-diameter ratios, and subcooling.

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

Report presenting an investigation to determine the normal force of two three-blade NACA propellers and the agreement of the measured normal force with a theoretical method. Propeller thrust and normal force were measured for a variety of blade angles, angles of attack, and Mach numbers. Results regarding variation with thrust, effect of inclination, and a comparison with theory are provided.

Memorandum presenting the effects of resin coating methods on some physical properties of laminates prepared with glass fabric, Fiberglas 181, and bonded with two commercial polyester resins. The resins used were Laminac 4126 and Selectron 5003. The resin coating methods used were roller coating, application of a dilute solution of resin, resin immersion, application of monomeric styrene, and vacuum impregnation.

Report presenting a compressor-rotor-blade vibration survey on a production turbojet engine incorporating a 13-stage axial-flow compressor with a pressure ratio of approximately 7 and an air flow of 120 pounds per second. The investigation was conducted due to the major problem that fatigue failures of compressor rotor blades have caused in the development of the axial-flow compressor. Results regarding rotating stall characteristics, rotor-blade vibration, and fourth-stage rotor-blade failure are provided.

Report presenting an investigation in the transonic blowdown tunnel at Mach numbers from 0.63 to 1.41 to determine increments in lift, drag, and pitching moment of a sweptback semicircular air inlet installed in the root of a 45 degree sweptback wing. Results regarding internal pressures and inlet performances are provided.

Report of an investigation of the effect of mode of engine operation, engine configuration, and airplane flight condition on the performance and design requirements of a turboprop engine with a high-pressure-ratio single-spool compressor. Both single-spool engines and gas-generating engines are considered. The free-turbine engine was found to be less versatile than the single-spool engine because the range of turbine-inlet temperature over which it can operate is restricted.

Report presenting testing of two beams of three web types which were loading in bending and subjected to rapid skin heating at rates from about 50 to 70 degrees Fahrenheit per second. The investigation was meant to determine some of the effects that rapid skin heating would have on the buckling and failing strength of multiweb-wing structures. The three types of web tested included the channel web, corrugated web, and truss web.

Report presenting a study of the application of Wiener filter theory to the design of a beam-rider guidance system operating in the presence of glint noise. The theory is then used to establish the theoretical lower limit of root-mean-square error and the corresponding desired transfer-function characteristics.

An investigation of the effects of jet nozzle geometry, size of base annulus, and base bleed upon the base and afterbody pressures of a cylindrical afterbody at transonic speeds has been conducted. Sonic and supersonic conical nozzles with jet-to-base diameter ratios from 0.25 to 0.85 were investigated with a cold jet at jet total-pressure ratios up to approximately 8.0 through a Mach number range from 0.6 to 1.25. Base pressure coefficients of about -0.55 were measured for the sonic nozzles at a Mach number of 1 or greater. The jet-to-base diameter ratio had a substantial effect on the base pressure obtained on the cylindrical afterbody of this investigation. Base bleed was beneficial in increasing the base pressure under certain conditions but had little or no effect at certain other conditions.

Report presenting the results of short-time creep-buckling and creep-bending tests of 2024-T4 aluminum-alloy columns of slenderness ratio 111 are presented. Tests were performed at 600 degrees Fahrenheit and strain measurements were taken with high-temperature electric-resistance strain gages.

Report presenting a cycle analysis of a turboprop engine for various modes of operation over a range of flight conditions in order to determine whether one mode of operation has any marked advantages. The methods of operation explored included constant compressor equivalent design speed, constant design engine rotative speed, adjustable turbine stators, and variable exhaust-nozzle area.

Report presenting a wind-tunnel investigation at low speed in the 300 mph 7- by 10-foot tunnel to determine the effect of deflector projection on the control effectiveness of spoiler-slot-deflectors on a 30 degree sweptback wing-fuselage model equipped with either a 15-percent-chord spoiler or a spoiler-slot-deflector. Results regarding the aerodynamic characteristics, wing longitudinal characteristics, rolling-moment characteristics, and pressure distributions are provided.

Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the effects of various external-store configurations on the longitudinal and lateral aerodynamic characteristics of a model of a 45 degree swept-wing fighter airplane. Results regarding accuracy and remarks on effects of stores are provided.

Memorandum presenting an investigation of the effects of stator cone angle and tip leakage on turbine performance. A single-stage turbine with 40-percent reaction was operated with two stators and two stationary shrouds. The turbine was operated at an entrance temperature of 660 degrees R with total-pressure ratios from 1.25 to 3.70 and equivalent mean blade speeds from 166 to 655 feet per second.

From Summary: "NACA research on afterburners for turbojet engines during the past 5 years is summarized. Although most of this work has been directed toward the development of specific afterburners for various engines rather than toward the accumulation of systematic data, it has, nevertheless, provided a large fund of experimental data and experience in the field. The references cited present over 1000 afterburner configurations and some 3500 hours of operation. In the treatment of the material of this summary, the principal effort has been to convey to the reader the "know-how" acquired by research engineers in the course of the work rather than to formulate a set of design rules."

"A preliminary low-speed investigation has been made of an air scoop submerged one-half the inlet height in a depression on the surface of a simulated fuselage. Boundary-layer suction was used on the steep approach ramp to improve the internal flow. A 6-degree-included-angle diffuser with an area ratio of 1.9:1 was located behind the inlet in the model. Most of the tests were conducted with an initial turbulent boundary layer believed to approximate that which would occur on the forward part of a fuselage" (p. 1).

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 in the stability tunnel to determine the combined effect of wing and wing-body interference on the contribution of an x-tail configuration to the low-speed rolling-stability derivatives of an airplane model with an unswept midwing and to indicate the change due to roll in the local flow angularity at a number of stations across the tail surfaces for one-half of the x-tail. Results regarding the static longitudinal characteristics, steady-roll characteristics, and angularity measurements are provided.