Report presenting a method by which incremental pitching moments can be estimated for swept and triangular wings with arbitrary types of trailing-edge high-lift flaps. Span-loading theory is combined with two-dimensional airfoil data adjusted for the effects of sweep. Application of the method is demonstrated for 58 cases covering various types of flaps on wings with a wide range of sweep, aspect ratio, and taper ratio.

Report presenting an investigation of boundary-layer bleed through a slot placed at the juncture of the suction surface and end wall to determine whether bleed in this manner could be used to prevent the local accumulation of boundary-layer fluids due to secondary flows. Results regarding the effect of bleed pressure, effect of bleed-slot height, and effect of slot length and position are provided.

Report presenting experimental flutter testing at Mach numbers up to 3.0 using cantilever-wing models with 0 to 60 degree sweepback and 60 degree delta-wing models. The main variables explored were the high Mach number and center-of-gravity location on flutter trends. The theoretical results for flutter analyses were noted to be lower than the experimental results.

"An exploratory investigation at Mach number 2.72 has been made to show the decrease in the drag of a round-nose model achieved by mounting a small cone on a rod ahead of the nose. The geometric parameters which were varied were the cone-base diameter, cone angle, and rod length. All models showed large decreases in drag compared to that of the round nose alone" (p. 1).

Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the static longitudinal and lateral stability and control characteristics of an 0.065-scale model of the Chance Vought Regulus II missile. The tests were made at three Mach and Reynolds numbers.

Report presenting the status of oscillating air forces, including forces, moments, and their respective phase angles for a 45 degree swept wing of aspect ratio 2 and for two bodies of revolution. Derivatives based on available analyses were also demonstrated for those three configurations.

Report presenting an investigation of a turbojet engine with variable inlet guide vanes in an altitude test facility to determine the steady-state compressor performance and surge characteristics. Compressor surge pressure ratios were found to be unaffected by changes in flight condition for either position of the inlet guide vanes. Decreasing the inlet Reynolds number was found to reduce the corrected fuel flow required for compressor surge.

"The flow-field characteristics around a swept-wing airplane model at low subsonic speed are described, and the loads induced on a typical missile model while operating within these flow fields are presented. In addition, theoretical flow fields are compared with experiment and are used in first-order estimations of the resulting induced missile loads" (p. 1).

Memorandum presenting an investigation of the problems associated with the design of a low-pressure-loss, short afterburner for sea-level thrust augmentation in a static, sea-level test stand. Results regarding diffuser pressure losses, afterburner pressure losses, and afterburner performance are provided.

Report presenting an investigation of the rolling-stability derivatives for a model of the Republic F-105 airplane over a range of Mach numbers and angles of attack. The model retained damping in roll through the test ranges, but values of the damping varied considerably with angles of attack. Derivatives of yawing moment and lateral force due to rolling generally followed previously indicated trends.

Report discussing testing to determine the longitudinal and lateral stability and control characteristics of a Chance Vought Regulus II missile at several Mach and Reynolds numbers.

Low-temperature chemical starting of combined JP-4 nitric acid propellant for low-thrust rocket engine using three-fluid propellant valve.

Memorandum presenting an assessment of the importance of the addition lag of the monowing versus a cruciform shape on a missile.

"The steady pressure loads as well as the temperature change on adjacent surfaces due to the presence of a propulsive jet at subsonic speeds is shown to be insignificant. Whereas at supersonic speeds the temperature effect might be expected to remain insignificant, the steady pressure loads were shown to increase greatly on surfaces downstream of the propulsive jet exit" (p. 1).

Memorandum presenting an analysis and evaluation of the meteorological requirements and problems anticipated with the operation of commercial turbojet aircraft. Discussions concerning problems of temperature, wind, pressure, ceiling, visibility, cloud and clear-air turbulence, icing, and communication are included in this study.

"The steady pressure loads as well as the temperature change on adjacent surfaces due to the presence of a propulsive jet at subsonic speeds is shown to be insignificant. Whereas at supersonic speeds the temperature effect might be expected to remain insignificant, the steady pressure loads were shown to increase greatly on surfaces downstream of the propulsive jet exit" (p. 1).

Report presenting an investigation at free-stream Mach numbers of 1.62, 1.94, and 2.41 to determine the external-drag effects and pumping characteristics of a short ejector housed within a highly bottailed afterbody. The tests covered secondary to primary diameter ratios of 1.50 and 1.33, mass flow ratios from 0 to 0.20, and a sonic and a supersonic primary nozzle. Results regarding drag and pumping characteristics are provided.

From Summary: "The effects of variation in inlet-air temperature, combustion pressure, and boron or pentaborane concentration on combustion performance were discussed. It was shown how the theoretical data herein could be employed in obtaining the combustion efficiency of experimental combustors. Data were presented by which combustion efficiencies obtained with a water-quench heat balance could be adjusted for the heat of dissociation of the combustion products."

Report presenting statistical measurements of landing-contact conditions for 144 landings of a heavy bomber airplane during routine daytime operations at Carswell Air Force Base. Using measurements obtained by a special photographic method, sinking speeds, bank angles, rolling velocities, and horizontal speeds at the instant before contact were evaluated and analyzed.

Report presenting a modification of an eight-stage high-pressure-ratio axial-flow compressor in order to improve design-speed performance and to provide an instrument for continued study of the problems associated with design and off-design performance of transonic stages combined with highly loaded subsonic stages. Results regarding the design point characteristics and predicted changes in compressor performance are provided.

Report presenting an investigation in the high-speed tunnel of the effects at high subsonic speeds of horizontal-tail height on the aerodynamic and loading characteristics in sideslip of a 45 degree sweptback, untapered tail assembly. Configurations investigated include the fuselage alone, the fuselage plus vertical tail, and with a horizontal tail mounted at 0, 50, and 100 percent vertical-tail span. Results regarding the lateral force coefficient, rolling-moment coefficient, and a comparison of experimental and theoretical results are provided.

Memorandum presenting an investigation of flow separation from a flat plate ahead of two blunt two-dimensional bodies in detail at Mach number 2. Interferograms were obtained for the separated regions, and the pitot-pressure distribution and flow directions were surveyed in one of the regions. Results regarding recovery factors and static pressures, density, total pressure, Mach number distribution, and flow-direction survey are provided.

Report presenting an investigation of NACA 8.75-(5)(05)-037 eight- and six-blade dual-rotating propellers under static conditions. The slipstream-boundary cone angle was found to agree with the theoretical angle of spread for an unheated jet. Results regarding the longitudinal survey, stationary survey, effect of blade angle, nature of flow near propeller, and effect of blade angle on slipstream rotation are provided.

Report presenting an investigation of the problems associated with the design of a low-pressure-loss, short afterburner for sea-level thrust augmentation in a static, sea-level test stand using the power section of a 5970-pound-thrust, axial-flow turbojet engine. The various portions of the afterburner and procedures used to test it are described. Results regarding diffuser pressure losses, afterburner pressure losses, and afterburner performance are provided.