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.

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.

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 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.

Boron and its hydrides offer increased flight range relative to conventional fuels for turbojet engines. Preliminary evaluation has been made of the combustion characteristics and deposition problems resulting from burning diborone in a single, modified J33 combustor. A combustor relatively free of deposits for the limited test conditions has been developed. Three possible methods of alleviating deposits on the turbine blades are reported.

Memorandum presenting a study of the spontaneous flammability of pentaborane and pentaborane-3-methylpentane blends. The behavior of the substances in air and in liquid and vapor states was studied. Results regarding conditions under which pentaborane did not ignite and conditions under which pentaborane did ignite are provided.

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.

During a free-jet investigation of a 28-inch ram-jet engine at a Mach number of 2.35, flow pulsation at the engine inlet were discovered which proved to have an effect on the engine performance and operational characteristics, particularly the engine rich blowout limits. This report discusses the finding of the flow pulsations, their elimination, and effect. Other facility characteristics, such as the establishment of flow simulation and the degree of subcritical operation of the diffuser, are also explained.

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.

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.

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 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.

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.

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 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.

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.