From introduction: This report details the results of the post-irradiation examination of a test involving one defected rod and one undefected rod.

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.

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.

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 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.