Report presenting an investigation of a full-scale, four-shock, side-inlet diffuser in a free-jet facility at a Mach number of 3.16. The diffuser was a heavy-duty version of the diffuser to be used with the XRJ47-W-7 engine. Results regarding the supercritical capture-area ratio, critical diffuser total-pressure recovery, and diffuser-exit flow profiles are provided.

Report presenting an investigation at Mach numbers of 1.61 and 2.01 to determine the pressure distributions for a series of 20 controls on a 60 degree delta wing. Tests occurred at a range of angles of attack and control deflections. Results regarding basic pressure distributions, comparison of experimental and theoretical results, and experimental comparisons are provided.

Report presenting an investigation at two Mach numbers to determine the pressure distributions for a series of 20 controls on a 60 degree delta wing. Thirteen controls were of the balanced tip type and seven of the controls were of the more conventional trailing-edge type. Results regarding the basic pressure distributions, comparison of experimental and theoretical results, and some experimental comparisons are provided.

Report presenting studies to determine the effect of sliding velocity and ambient temperature on the friction properties and endurance lift of thin lead monoxide coatings bonded to type 440-C martensitic stainless steel. Results regarding the effect of run-in on endurance life are also provided.