Report discussing the effects of suction through slots at the .5 percent chord and 2.5 percent chord stations on the longitudinal aerodynamic characteristics of a 47.5 degree sweptback wing-fuselage configuration with and without flaps. Information about the Reynolds number effects, characteristics of the plain wing, wing with split flaps, extensible leading-edge flaps, the effect of power failure, and the drag coefficients is provided.

Report presenting an experimental investigation in a one-sixth sector of an annular turbojet combustor to determine a method of controlling radial exhaust-gas-temperature distribution in a gas-turbine combustion chamber. The adjustment in controlling air was made by ducting the dilution air into the combustion zone in a predetermined manner through hollow radial struts or by modifying the basket-wall open-hole area. Results regarding the temperature distribution, temperature-rise efficiency, total-pressure loss, and altitude operating limits are provided.

Report presenting the results of lift, drag, and pitching-moment measurements on a model of the Douglas D-558-2 airplane at a range of angles of attack and Mach numbers. The model was also tested with two different sets of chordwise fences in order to investigate their effects on force and moment characteristics at high speeds.

Report presenting testing of two two-blade propellers in the 8-foot high-speed tunnel for a range of blade angles and Mach numbers. The results show that changes in thrust loading due to compressibility effects were much smaller for the thin-blade propeller than for the thick-blade propeller.

Report presenting an investigation in the 16-foot transonic tunnel to determine the effects of leading-edge slats on the aerodynamic and longitudinal stability characteristics of a model of a swept-wing fighter-type airplane. Two different spanwise extents of leading-edge slats were tested, from 35 to 95 percent semispan and from 46 to 95 percent semispan. Results regarding the lift characteristics, drag characteristics and lift-drag ratios, stability characteristics, and flow-study pictures are provided.

From Introduction: "The investigation is discussed in the present report is an analysis of the turbojet engine as the power plant for bombers capable of supersonic flight speeds. A similar analysis, in which the turbojet engine is considered for the propulsion of supersonic fighter aircraft, is presented in reference 1. Two plans are considered in this report."

Memorandum presenting the effects on combustor performance of operation at the high inlet-air pressures, temperatures, and velocities representative of conditions that may be encountered in high-pressure-ratio turbojet engines or at high flight speeds studied in a single tubular combustor. Some of the performance characteristics investigated were combustor-liner temperatures, carbon deposition, smoke formation, and combustion efficiency.

Report presenting an investigation to determine the effects of inlet-annulus blockage on compressor performance and its corresponding effect on the computed performance of a hypothetical engine. The hypothetical engine performance was calculated from the overall compressor performance and assumed component performance characteristics. Results regarding the compressor performance with no inlet blockage, effect of hub blockage on compressor performance and stall characteristics, effect of sector blockage on compressor performance, effect of hub blockage on computed engine performance, and design and control problems are provided.

Report presenting detailed circumferential and radial surveys of total pressure and total temperature made downstream of the turbine rotor of a high-speed, high-specific-mass-flow turbine at design operating conditions. The purpose of this testing was to determine the sources and magnitudes of losses in turbines. Results regarding total pressure ratio, total-temperature-drop ratio, contours of efficiency, and location of the losses are provided.

The gust and draft velocities from records of NACA instruments installed in P-61C airplanes participating in thunderstorm flights at Clinton County Army Air Field, Ohio, from September 10, 1947 to September 15, 1947, are presented.

From Summary: "This report presents the results of wind-tunnel force tests which were conducted to determine the low-speed stability and control characteristics of a full-scale Northrop XSSM-A-3 missile. Tests were made through a range of angles of attack, sideslip, and control deflection, and at various Reynolds numbers. Characteristics of the complete missile are compared with the characteristics of the missile with the landing skids extended, with the vertical tail removed, and with the fuselage alone. No analysis of the data has been made in order to make the results available as soon as possible."

An investigation was conducted to determine the effect of electropolishing precision-forged blades and of machining blades from oversize forgings on the engine performance of Nimonic 80 and Nimonic 80A turbine blades. These blades, along with precision-forged blades, were run in a J33-9 turbojet engine. The tests resulted in the following conclusions: (1) Electropolishing of precision-forged blades did not improve engine life relative to the life of nonelectropolished blades. (2) Machining blades from oversize forgings did not improve the engine life of precision-forged blades. (3) The precision-forging and heat-treating practice used in fabricating the blades investigated was such that the surface roughness and oxide penetration was so slight, approximately 0.0005 inch in depth, as to preclude any benefits derived from surface removal by electropolishing or machining.

"Experimental results showing the static longitudinal-stability and control characteristics of a model of a fighter airplane employing a low-aspect-ratio unswept wing and an all-movable horizontal tail are presented. The investigation was made over a Mach number range from 0.60 to 0.90 and from 1.35 to 1.90 at a constant Reynolds number of 2.40 million, based on the wing mean aerodynamic chord. Because of the location of the horizontal tail at the tip of the vertical tail, interference was noted between the vertical tail and the horizontal tail and between the wing and the horizontal tail" (p. 1).