Memorandum presenting a theory for evaluating the mutual interference between a wing and tip tank as extended to apply to store-pylon configurations. By using the theory and the flow-field formulas of a previous report, theoretical store-pylon side-force estimates have been made for a number of store-pylon configurations. Results regarding the theory for store-pylon side force, scope of test configurations, contribution of store and pylon to combined load, effect of store spanwise location on the store-pylon side-force coefficient, effect of pylon sweep and store chordwise location, effect of sideslip on the store-pylon side-force coefficient, effect of fins on store side-force coefficient, and interference effects between inboard and outboard stores are provided.

"Several materials have been tested in the ceramic-heated jet (laboratory model) at a Mach number of 1.96 with a stagnation temperature of approximately 4,000 degrees Fahrenheit. Test models made of molybdenum were less affected by temperature than titanium, stainless steel, and an alloy of 90 percent tungsten, 6 percent nickel, and 4 percent copper. Titanium and steel burn with highly exothermic reactions when subjected to the 4,000 degrees Fahrenheit air jet" (p. 1).

Report presenting an investigation in the full-scale tunnel to determine the effects of boundary-layer control by blowing over trailing-edge flaps on the low-speed performance and static longitudinal stability characteristics of a 60 degree delta wing-body-tail combination with variable flap positioning and leading-edge devices. Results regarding the flap lift characteristics at zero angle of attack, tail-off characteristics, tail-on characteristics, and low-speed performance characteristics are provided.

Report presenting pressure distributions associated with stable combustion of aluminum borohydride in the supersonic stream adjacent to a short, 13-inch chord, and an extended, 25-inch chord, flat-plate model. High-speed direct and schileren motion pictures of the flame and associated shock waves were taken. Results regarding the description of the combustion and associated stream disturbances, static-pressure change at model reference surface caused by combustion, lift forces resulting from combustion, base pressure change caused by combustion, stream-parameter measurements during combustion, and surface temperature changes during combustion are provided.