Report presenting a pressure-distribution investigation of a parabolic body of revolution with a fineness ratio of 12.2, which was performed in the 4- by 4-foot supersonic tunnel at Mach number 1.59 and Reynolds number 3.6 x 10(sub 6), based on body length, for a range of angles of attack. Results regarding basic pressures, aerodynamic coefficients, asymmetrical pressures, comparison of experimental and theoretical pressures, artificial roughness, section coefficients, and body coefficients are provided.

Report presenting testing regarding the Bell X-2 supersonic research airplane, which is equipped with a skid main landing gear and nose wheel, to determine the low-speed handling qualities and landing characteristics. Results regarding the landing approach pattern, time histories, and final resting position of the airplane at landing are provided.

Report discussing testing in the low-turbulence tunnel to determine the effectiveness of several configurations of vortex generators in increasing maximum lift of a 6-percent-thick symmetrical circular-arc airfoil section. None of the configurations tested were found to greatly increase the lift. Some of the configurations tested included a single row of vortex generators, two rows of generators, larger vortex generators, and sweeping forward the front row of generators.

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 an investigation at low speed in the Langley full-scale tunnel of the downwash, sidewash, and wake behind a large-scale 60 degree triangular wing with 10-percent-thick biconvex airfoil sections. Results regarding the air-stream surveys for three different configurations and stability and trim are provided.

Report presenting an investigation of inlets utilizing two-dimensional compression wedges mounted normal to the fuselage surface with ram-type scoops for partial removal of the boundary layer. Two compression-wedge angles were included to simulate fixed positions of a variable-geometry configuration. Results regarding supersonic performance characteristics and subsonic and take-off performance characteristics are provided.

Report presenting the specific impulse, characteristic velocity, thrust coefficient, and heat rejection of liquid fluorine and a fuel consisting of a hydrazine-ammonia mixture for a range of fuel percentages in a 100-pound-thrust rocket engine designed for a combustion-chamber pressure of 300 pounds per square inch absolute. The fuel consisted of 59 percent hydrazine, 37 percent ammonia, and 4 percent water. The attainment of maximum performance with liquid fluorine as a rocket oxidant will require a critical study of injector design.

Report presenting testing of JP-3 fuel and a slurry of 60 percent powdered magnesium in JP-3 fuel in a small-scale afterburner in the presence of large quantities of water vapor. The results indicated that total temperature, combustion efficiency, and air specific impulse were improved when the magnesium slurry was used, but the improvements came at the cost of increased liquid consumption.

Report presenting an investigation of the effect of fuselage-mounted rocket boosters on a strut-mounted engine in the 8- by 6-foot supersonic wind tunnel at Mach numbers of 1.8 and 2.0. The boosters were pairs of circular cylinders with conical forebodies mounted on the top and bottom of the fuselage, and the engine was mounted on a horizontal strut. Results regarding the characteristics of the flow field, effect of putting the boosters in several positions, and effect of angle of attack are provided.

Memorandum presenting an investigation of the influence of blade-row geometry on secondary flows in a two-dimensional cascade by varying independently stagger angle, aspect ratio, solidity, and angle of attack and by providing blade fillets. Stagger angle and aspect ratio had no appreciable effect on this secondary flow, whereas solidity and angle of attack did affect the flow patterns indicating the turning as a major parameter.

Report presenting a free-flight investigation of a rocket-powered control research model to determine the force and hinge-moment characteristics of a half-delta tip control on a delta wing. Results regarding the control hinge moments, control normal force, and total normal force are provided.

Report presenting an investigation at high and low subsonic Mach numbers of two symmetrical 6-percent-thick airfoil sections derived to have high maximum lift at low speeds. The high-speed portion of the investigation included lift, drag, and pitching moment measurements.

Report discussing an investigation into the effects of camber and leading-edge-flap deflection on the pressure pulsations on thin rigid airfoils at a range of Mach numbers. The ideal camber or flap deflection was found to be dependent on Mach number and normal-force coefficient. The results of this testing, which used a 64A006 airfoil, was compared to previous testing using a 65A006 airfoil.

Report presenting an investigation in the supersonic blowdown tunnel to determine the effects of external store location on the lift, drag, and pitching-moment characteristics of a 60 degree delta wing at Mach numbers of 1.41, 1.62, and 1.96. Brief comparative tests were also made to determine the effect of changing the sweep of the strut attaching the store to the wing and of changing the chordwise location of the swept strut.

Report presenting an investigation in the transonic blowdown tunnel from Mach numbers 0.80 to 1.41 to determine the increments in lift and drag due to installation of a triangular-shaped air inlet in the root of a 45 degree sweptback wing and to determine the internal flow characteristics of the inlet. Results regarding pressure measurements of the inlet model, force measurements of basic and inlet models, and effect of boundary-layer bypass scoop and fuselage nose configuration on characteristics of inlet model are presented.

From Summary: "A supersonic free-jet facility (Mach number 3) capable of accommodating full-scale ram-jet engines has been constructed and evaluated. A 24-inch circular nozzle produces a jet of sufficiently uniform velocity that a good simulation of the engine internal flow is obtained. An annular diffuser placed around the engine recovers part of the total pressure of the jet flow passing outside the engine so that the pressure ratios which must be imposed across the facility to start and maintain the jet are kept to reasonable values."

Report presenting an investigation in the high-speed tunnel to determine the effect of leading-edge shape and section profile on the aerodynamic characteristics of two thin wings of aspect ratio 4. Lift, drag, and pitching-moment data are presented for a range of angles of attack and Mach numbers. Information about a third wing with an aspect ratio of 3, a taper ratio of 0.4, and a 4.5-percent-thick modified-hexagonal section are also provided.

"A flowmeter has been developed which combines a volume-time measurement of the flow, regulation of the rate, and a determination or presetting of the pressure head producing the flow. This meter is capable of accurately metering and controlling very small rates of gas flow within a closed system such as those required in a small capillary tube gas viscosimeter" (p. 1).

"The Bell X-2 supersonic research airplane is equipped with a skid main landing gear and a nose wheel. Pending completion of the rocket engine, glide flights are being performed to determine low-speed handling qualities of the airplane and the landing characteristics with the skid-type landing gear. The present paper presents data obtained during the approach and landing of the X-2 airplane on its first flight" (p. 1).

Report presenting an investigation to determine the dynamic stability and control characteristics of a scale flying model of the Consolidated-Vultee XFY-1 vertically rising airplane. It includes the results of flight tests to determine the stability and control characteristics of the model in hovering, take-offs, and landings.

Memorandum presenting an investigation of a half-delta wing-tip control on a semispan 60 degree delta-wing-fuselage combination conducted in the 9- by 12-inch supersonic blowdown tunnel. Control-surface hinge moments and bending moments, as well as the characteristics of the complete wing-fuselage combination, were obtained over a large range of control deflection and angle of attack at specified Mach and Reynolds numbers. Results regarding the control bending-moment and hinge-moment characteristics, control effectiveness characteristics, and effect of fence on wing characteristics are provided.

Report discussing testing of a model of a cruciform 60 degree delta-wing missile configuration with half-delta tip controls at a range of Mach numbers. Longitudinal stability derivatives, control effectiveness, and drag characteristics were obtained using a square-wave pulsed-control technique.

Report presenting an investigation of the planing characteristics of various combinations of a wheel and a hydro-ski. Models tested included at least two values of the following parameters: diameter of wheel, width of wheel, cross-section shape of wheel, fore-and-aft location of wheel, lateral location of wheel, gap between wheel and ski, rotation of wheel, and protrusion of wheel. Results regarding the general effect of a wheel, effect of wheel shape and size, effect of wheel-ski arrangement, and possible methods of reducing resistance are provided.

Report presenting a study of the altitude-starting limits of a production turbojet engine with an axial-flow compressor and a multiple through-flow combustor. The ignition limits, flame-propagation limits, and acceleration limits of the engine were improved to increase the starting limits to relatively high altitude.