Report presenting an investigation of a pylon-mounted-store airplane configuration in the supersonic pressure tunnel at a Mach number of 1.61. Forces and moments of a complete wing-fuselage-store-pylon combination was measured for a variety of pylon-mounted store locations below the wing. Results regarding the effect of store position on the aerodynamic characteristics in pitch, effect of store position on the aerodynamic characteristics in sideslip, store fins and store tail cone, double-store installation, effect of pylon location, and relative contribution of store-pylon forces toward total force are provided.

Memorandum presenting an experimental investigation of the pressure-recovery performance of a fixed-geometry, two-cone, two-drag inlet at Mach number 2.95. Low drag was achieved by use of an internally cylindrical cowl with rapid flow turning that was within 4 degrees of the wedge angle for shock detachment. Results regarding the inlet performance and evaluation of inlet performance are provided.

Report presenting aerodynamic forces for an external-store installation on the Douglas D-558-II research airplane. Store-pylon, pylon-alone, and fin loads were determined during angle-of-attack and angle-of-sideslip maneuvers over a range of Mach numbers. Results regarding the side-force coefficients, normal-force coefficients, external-store-load parameters, external-store fin loads, and wing-panel aerodynamic loads are provided.

Report presenting preliminary flight surveys of noise inside fuselages and in the fuselage boundary layer, which were obtained in order to determine the magnitude of the noise and relative importance of engine noise and noise due to the boundary layer. Results indicated that the sound-pressure level continued to increase with airspeed to the highest airspeed obtained, although the rate of increase at supersonic speeds was less than at subsonic speeds. Testing occurred on the B-47A and D-558-II airplanes.

Report presenting the results of an investigation of the static longitudinal stability and control characteristics of a canard airplane configuration without analysis over a range of Mach numbers. Data are presented for various combinations of the body, canard, wings, and vertical tail at 0 and 5 degrees of sideslip over a range of angles of attack and canard deflection angles.

Report presenting an experimental investigation of a rectangular swept scoop inlet designed for and tested at a free-stream Mach number of 3.1 to determine the effect of inlet aspect ratio on the minimum inlet starting concentration ratio and the resulting inlet total-pressure recovery. Results regarding the determination of the starting contraction ratio, effect of inlet aspect ratio on the inlet starting characteristics, total-pressure recovery and mass-flow variations, and effects of inlet aspect ratio on the maximum total-pressure recovery are provided.

A brief investigation of a target-type thrust reverser on a single-engine fighter model has been conducted in the Langley 16-foot transonic tunnel at Mach numbers from 0.20 to 1.05. At Mach numbers of 0.80, 0.92, and 1.05, a hydrogen peroxide turbojet-engine simulator was operated with the thrust reverser extended. The angle of attack was varied from 0 degrees to 5 degrees at these Mach numbers.

Memorandum presenting a five-stage rocket-propelled model flown up to a Mach number of 10.9 and a corresponding free-stream Reynolds number of 6.57 x 10(exp 6) based on nose diameter. Temperatures were measured at 16 stations on the inside of a flat-faced cylinder made of copper. Results regarding the flight test, wall temperatures, heat-transfer data, measurement repeatibility and effects of angle of attack, comparison of measured and theoretical stagnation-point heating rates, and measured and theoretical heating rates over the front and side of the nose are provided.

Report presenting pressures measured during a free-flight test at zero angle of attack over a rocket model with a modified Von Karman nose in combination with a cylindrical center section and a 10 degree half-angle flare.

Report on an investigation to determine the erect and inverted spin and recovery characteristics of a model of the North American FJ-4 airplane. The testing found that either a flat-type of steep-type spin may be obtained when the airplane is spinning erect. The optimum recovery technique from inverted spins was full rudder reversal with simultaneous movement of the ailerons to full with the stick maintained full forward.

Memorandum presenting the effect of free-stream Reynolds number, engine installation, and model scale on inlet stability limits and on the amplitude and frequency of buzz. The data were taken at a free-stream Mach number of 2.0 and angles of attack from 0 to 6 degrees. Results regarding free-stream Reynolds number effect, model scale, and effect of engine on stability are provided.

Report presenting the effect of free-stream Reynolds number, engine installation, and model scale on inlet stability limits and on the amplitude and frequency of buzz. The data was obtained at mach number 2.0 and a range of angles of attack. Results regarding the free-stream Reynolds number effect, model scale, and effect of engine on stability are provided.

Report presenting an investigation of a two-stage turbine with a downstream stator to determine the interstage flow conditions of the turbine. Results regarding stage efficiency and work output, first-stage performance, second-stage performance, and downstream-stator performance are provided.

Memorandum presenting an investigation of the thermal stability of a commercial grade of propyl pentaborane at temperatures of 147 and 190 degrees Celsius. The products of decomposition are hydrogen, hydrocarbons, and a solid nonvolatile yellow boron hydride.

Memorandum presenting an investigation of the thermal stability of a commercial grade of propyl pentaborane (HEF-2) at temperatures of 147 and 190 degrees Celsius. The products of decomposition are hydrogen, hydrocarbons, and a solid nonvolatile yellow boron hydride. An equation is provided that can be used to calculate the approximate time required to decompose 20 percent of propyl pentaborane at other temperatures.

Memorandum presenting a study of the performance of swirl-can combustor elements for an experimental short-length turbojet combustor utilizing hydrogen fuel at high-altitude operating conditions. Fuel was injected into each element through a tangential, sonic orifice that created a swirling fuel-air mixture within each element. Results regarding combustor blowout, combustion efficiency, outlet temperature distribution, and preliminary performance of multielement combustor are provided.

Report presenting a study of the performance of "swirl-can" combustor elements for an experimental short-length turbojet combustor utilizing hydrogen fuel at high-altitude operating conditions. Fuel was injected into each element through a tangential , sonic orifice that created a swirling fuel-air mixture within the element. Results regarding combustor blowout, combustion efficiency, outlet temperature distribution, and preliminary performance of the multielement performance of multielement combustor are provided.

Memorandum presenting the performance of a scoop-type inlet on the bottom of a body of revolution at several Mach numbers and angles of attack. The investigation included a study of the effects of altering the approach surface ahead of the inlet, extending the boundary-layer splitter plate, and bleeding air at the throat and exit of the diffuser.

Memorandum presenting a study of the performance of a scoop-type inlet on the bottom of a body of revolution at a range of Mach numbers and angles of attack to 10 degrees. The investigation included a study of the effects of altering the approach surface ahead of the inlet, extending the boundary-layer splitter plate, and bleeding air at the throat and exit of the diffuser. Results regarding the flow survey ahead of the inlet, alternative configurations, internal-flow details of the basic configuration, air bleed at the throat, and air bypass at the engine face are provided.

Report presenting testing of several underslung scoop-type inlets mounted on a body of revolution at several Mach numbers through a range of angles of attack. Geometric differences between inlets included ramp angle, frontal area, splitter-plate height, and aspect ratio. Results regarding inlet stability, peak pressure recoveries, and total-pressure distortions are provided.

The use of a magnetic field to control the motion of electrically conducting fluids is studied. The incompressible boundary-layer solutions are found for flow over a flat plate when the magnetic field is fixed relative to the plate or to the fluid. The equations are integrated numerically for the effect of the transverse magnetic field on the velocity and temperature profiles, and hence, the skin friction and rate of heat transfer. It is concluded that the skin friction and the heat-transfer rate are reduced when the transverse magnetic field is fixed relative to the plate and increased when fixed relative to the fluid. The total drag is increased in all of the areas.

Report presenting an investigation of the performance of pentaborane fuel in a flight-type, 9.75-inch-diameter ramjet engine mounted in a connected-pipe altitude facility. Combustor efficiency was above 85 percent throughout the range of test conditions. Results regarding the connected-pipe performance and estimated flight performance are provided.

Report presenting a flight investigation to determine the static-pressure errors for nose-boom airspeed installations of 17 airplanes. Both research-type and service-type aircraft are covered in the investigation. Results indicated that the magnitude of static-pressure errors for the airspeed installations of all the airplanes is shown to vary with airplane geometric characteristics that include nose-boom length, fuselage diameter, and nose fineness ratio.

Report presenting the cloth permeability of rolling a tapering thickness on a 20x200-mesh stainless-steel wire clothing investigated experimentally. The application of the cloth was for the shell of a transpiration-cooled turbine blade operating at gas and shell temperatures of 2500 and 10000 degrees Fahrenheit. Results regarding the taper-rolled cloth and comparison of taper-and flat-rolled samples are provided.