Testing was conducting to evaluate the effects of support interference on the drag characteristics of two bodies of revolution at zero angle of attack at Mach number 1.5. Drag and base-pressure measurements are made for a variety of Reynolds numbers to determine the effect of varying the length or diameter of the rear support.

Report presenting a flight investigation to determine the comparative performance of AN-F-58 and AN-F-32 fuels in a 4000-pound-thrust turbojet engine. The fuels were equivalent over the range of conditions investigated. Results regarding corrected net thrust, corrected jet-fuel consumption, variation of corrected tail-pipe temperature, combustor blow-out speeds, and visual observations of the jet exhaust are provided.

Memorandum presenting preliminary tests in order to determine the effect of forced ventilation on the hydrodynamic characteristics of a scale model of a streamline fuselage of a hypothetical transonic airplane. The forced ventilation consisted of air ejected at about 300 feet per second through small orifices distributed over the fuselage bottom in a series of patterns simulating chines or multiple steps. Results regarding resistance, effective hydrodynamic lift, trim, spray, and air flow are provided.

Given here are results of tests made in calm water at various landing attitudes, speeds, and simulated conditions of damage. It was concluded that the best ditching could be made by contacting the water as near the stall angle as possible without losing adequate control. The landing flaps should be full down. If the paratainer hatch and aft-cargo doors fail as expected in a ditching, there will be a large inrush of water into the cargo compartment which makes this location a very hazardous ditching station. The airplane will settle in the water rapidly to the level of the wings with only gradual changes in attitude. The maximum longitudinal deceleration will be between 1.2g and 1.7g in a calm-water ditching.

Memorandum presenting a method for computing the isentropic and actual enthalpy change between the inlet and outlet of a centrifugal-flow compressor when water injection is used. The method of calculation is based on fluid property values given in steam and air tables.

Report presenting an investigation to determine the lift, drag, and pitching-moment characteristics of the NACA 0010 and 0010-64 airfoil sections at Mach numbers up to 0.91 and for a range of Reynolds numbers.

Report presenting an investigation to determine the possibility of delaying at moderate or large lift coefficients the onset of the abrupt supercritical drag rise of an airfoil section by the use of camber. Results indicated that the addition of camber to the NACA 0010 airfoil leads to significant improvements in the drag characteristics at moderately supercritical speeds .

Report presenting the results of an investigation in the full-scale tunnel of the static longitudinal stability and control of a convertible-type airplane as affected by articulated- and rigid-propeller operation. The investigation included force measurements for a large angle-of-attack range with the all-movable horizontal tail installed and removed.

Memorandum presenting the low-speed lateral control characteristics of a 32 degree sweptforward wing of aspect ratio 5.8 and NACA 65-series airfoil sections as determined in the 19-foot pressure tunnel. The investigation include the measurement of the hinge-moment and normal-force characteristics of an aileron and the rolling-effectiveness characteristics of the aileron and several configurations of spoilers.

From Summary: "Results of wind-tunnel tests are presented for a wing with the leading edge swept back 63^o and of symmetrical section in combination with a body at Mach numbers from 0.5 to 0.95 and from 1.09 to 1.51."

Report presenting results from a tank investigation of a powered dynamic model of the Grumman JRF-5 airplane fitted with a single hydro-ski and extended afterbody. Results indicated that the afterbody extension in place of a tail ski reduced the maximum resistance by 10 percent. Removal of the wing-tip skids gave a further reduction in maximum resistance of 3 percent.

Report presenting an attempt to determine the reliability and calibration of the Langley transonic tunnel in the open slotted test section. Results regarding test-section calibration, including flow uniformity, calibration, and angularity, model testing and boundary interference, and reduction of interference are provided.

Report presenting rolling effectiveness and drag tests of spoilers on unswept wings over a range of Mach numbers using rocket-propelled test vehicles in free flight. The wings tested had an aspect ratio of 3.7, were unswept and untapered, had thickness ratios of 3, 6, and 9 percent, and covered a range of flexibilities. Results regarding the rolling effectiveness and drag are provided.

Report presenting results of pressure-distribution measurements at low speed on a wing-fuselage combination with a wing of W plan form with aspect ratio 6, 45 degrees sweep, taper ratio 0.6, and an NACA 65A009 airfoil section placed parallel to the plane of symmetry. Results regarding aerodynamic characteristics, pressure distribution on the wing, pressure distribution on the fuselage, aerodynamic section characteristics, and stall patterns are provided.

Report presenting a low-speed investigation in the stability tunnel to determine the static longitudinal stability and control characteristics of two wing-fuselage combinations equipped with wing-tip controls of half-diamond and half-delta plan form. Results regarding the effect of control area and plan form on control characteristics and on trim characteristics are provided.

Memorandum presenting tests in the 9-inch supersonic tunnel to investigate the factors that determine the magnitude of the wing-tail interference effects on the static longitudinal stability of supersonic missile configurations with low-aspect-ratio, tandem, cruciform lifting surfaces and to develop a missile configuration with a minimum variation in static margin due to wing-tail interference effects.

Report presenting an investigation of three air inlets designed for use at transonic speeds conducted in the 8-foot high-speed tunnel. The basis of the design of the inlets was the use of a nose which was shaped so that substream velocities are maintained on its surface for high-speed operating conditions. Results regarding impact pressure recovery, external pressure distributions, wake-survey drag, supersonic external pressure drag, and design considerations are provided.

Report presenting an investigation of a model of an ejectable pilot seat combination with and without stabilizing fins. The main purpose of the investigation was to determine the static aerodynamic characteristics and effectiveness of various stabilizing fins at a high subsonic Mach number. Results regarding stability and force characteristics for the combinations are provided.

Report presenting an investigation by the wing-flow method to determine the snaking characteristics of a scale partial-model of a research airplane. Additionally, the snaking characteristics of 11 modified configurations of the research-airplane model were determined as well as a model that had a greater fineness ratio.

Report presenting pressure fluctuations measured near the trailing edge of the wing and near the leading edge of the tail of a scale model of the X-1 airplane with a 10-percent-thick wing in the 16-foot transonic tunnel. Results regarding frequency analyses are also provided.

Memorandum presenting an investigation in the Lewis laboratory to obtain pressure-drop data for flow of air with no heat addition through mockups of two reactor segments of the proposed GE aircraft reactor. Pressure-drop data were obtained over a range of Reynolds numbers, air inlet Mach numbers, inlet pressure, and ambient air temperatures. The results indicate that the friction factors, corrected for entrance, vena contracta, momentum, and exit losses are considerably higher at high Reynolds number than those reported for turbulent flow in smooth pipes.

Report presenting boundary-layer measurements on rocket-powered free-flight models to determine average skin-friction coefficients. The test body, NACA RM-10, was a fin-stabilized parabolic body of revolution of fineness ratio 12.2 with a blunt base to provide space for a rocket jet. Results regarding the skin-friction and boundary-layer profiles and experimental and theoretical curves are provided.

Report presenting an analysis of a number of free-flight transient responses resulting from small stabilizer movements obtained during testing of the Bell X-1 airplane to obtain its longitudinal stability characteristics. A comparison of flight data and model test data is also provided.

Memorandum presenting the results of a theoretical investigation of the lateral response and stability characteristics of the X-3 research airplane (Douglas Model No. 499D). Included are time histories calculated by a computer showing the effect of various disturbances on the lateral response of the airplane with 0 degrees geometric dihedral and -5 degrees dihedral.