Report presenting a summary of NACA research on afterburners for turbojet engines during the past 5 years. The references present over 1000 afterburner configurations and about 3500 hours of operation. The report covers the following topics: burner-inlet diffusers, fuel-injection systems, flameholders, combustion space, combustion instability, starting and transient performance, effects of diluents, and burner-shell cooling.

Report discussing testing on the drag, longitudinal stability, and lateral stability characteristics of a model of the McDonnell F4H-1 airplane. The minimum drag coefficients, neutral point, horizontal-tail-incidence range, static directional stability, and effective dihedrals are presented.

Report presenting an investigation of zero-lift drag of a fin-stabilized wing-body combination from high-subsonic to supersonic speeds in a range of Reynolds numbers. The wing was unswept about the 74.5-percent-chord line, an aspect ratio of 3.04, a taper ratio of 0.394, and 4.5-percent-thick modified hexagonal airfoil sections. Results regarding total drag, wing-plus-interference drag, and base pressure 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."

"An extended analysis was made of the previously reported performance investigation of the original compressor from the XJ-41-V turbojet engine and a similar compressor revised a to obtain a 33-percent increase in the geometric passage area at the vaned-collector entrance. This analysis was based on the concept of the vaned-collector entrance as the throat section of a nozzle. Because of nonuniform air distribution at the vaned-collector entrance, approximately 90 percent of the available flow area was utilized in the original compressor and 94 percent in the revised compressor" (p. 1).

From Summary: "Flight tests have been made to determine the longitudinal stability and control and stalling characteristics of a North American P-51H airplane. The results indicate that the airplane has satisfactory longitudinal stability in all the flight conditions tested at normal loadings up to 25,000 feet altitude. At Mach numbers above 0.7, the elevator push force required for longitudinal trim decreased somewhat because of compressibility effects."

"Spatial burnout calculations have been made of two types of water moderated cylindrical reactor using boron as a burnable poison to increase reactor life. Specific reactors studied were a version of the Submarine Advanced Reactor (sAR) and a supercritical water reactor (SCW). Burnout characteristics such as reactivity excursion, neutron-flux and heat-generation distributions, and uranium and boron distributions have been determined for core lives corresponding to a burnup of approximately 7 kilograms of fully enriched uranium" (p. 1).

Report presenting the results of a wind-tunnel investigation to determine the effects of a variation in wing taper ratio on the longitudinal characteristics of a wing-body combination at a variety of Mach numbers. The wings had an aspect ratio of 3, an unswept midchord line, and an NACA 64A003 profile. Results regarding the lift and pitching-moment characteristics and drag characteristics are provided.

"The influence of triangular-shaped end plates on the lift and the flow field of a canard-type control surface mounted on a symmetrical fuselage was investigated in the Lewis 8- by 6-foot supersonic wind tunnel at a Mach number of 2.00, body angle of attack of 2 degrees, and control-surface deflection angles of 3 degrees, 6 degrees, 8 degrees, and 10 degrees. The investigation demonstrated that the addition of end plates to a canard-type control surface increased its lift and rearranged the single vortex into a two-vortex system. Perforating the end plates reduced these effects and resulted in a decrease in lift and a change in the flow-field characteristics" (p. 1).

Force and pressure-recovery characteristics of a nacelle-type conical-spike inlet with a fixed-area bypass located in the top or bottom of the diffuser are presented for flight Mach numbers of 1.6, 1.8, and 2.0 for angles of attack from 0 degrees to 9 degrees. Top or bottom location of the bypass did not have significant effects on diffuser pressure-recovery, bypass mass-flow ratio, or drag coefficient over the range of angles of attack, flight Mach numbers, and stable engine mass-flow ratios investigated. A larger stable subcritical operating range was obtained with the bypass on the bottom at angles of attack from 3 degrees to 9 degrees at a flight Mach number of 2.0. At a flight Mach number of 2.0, the discharge of 14 percent of the critical mass flow of the inlet by means of a bypass increased the drag only one-fifth of the additive drag that would result for equivalent spillage behind an inlet normal shock without significant reductions in diffuser pressure recovery.

Memorandum presenting testing of an NACA 65(sub 06)A004 airfoil to determine the effects of a solid-strip spoiler on buffeting forces. Fluctuations of both section normal-force coefficient and of section pitching-moment coefficient are presented as functions of angle of attack and of section normal-force coefficient. Generally, the spoiler decreased the fluctuating section normal-force and pitching-moment coefficients if comparison is made at constant angle of attack and increased these coefficients if comparison is made at constant section normal-force coefficient.

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 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 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 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 the zero-lift drag characteristics of seven nose shapes on a slender body of revolution in free flight between the Mach numbers of 0.7 and 1.3. Some of the nose shapes included a spherical segment, flat face with a sharp shoulder, flat face with a rounded shoulder, 30 degree and 40 degree total-angle cones, and a spherical segment with two different length spikes. Results regarding drag coefficients and performance for the various shapes are provided.

Memorandum presenting the effects of variations in cooling-passage geometry on the relations between heat flow and temperature drops within liquid-cooled turbine blades. Wall thicknesses, blade section depths, and cooling-passage sizes, shapes, and spacings were varied experimentally on a simple electric analog on which are simulated rectangular sections of blades. Results are presented in terms of temperature differences between the cooled-surface temperature and average heated-surface temperature, minimum heated-surface temperature, maximum heated-surface temperature, and maximum temperature at the centerline of the turbine blades.

Report presenting an investigation of the effect of wing-mounted external stores on the loading and aerodynamic characteristics in pitch of a 45 degree sweptback wing combined with a fuselage. Store arrangements investigated consisted of stores mounted at the wing tips, stores mounted inboard on the wing undersurface at 46-percent semispan, and stores in both the tip and inboard locations.