Report describing the optical system of a new-type interferometer utilizing schileren optics. Using this instrument, former limits to the working-field size imposed by the practical size of conventional topics are removed. Testing using the interferometer occurred in the 18- by 18-inch supersonic tunnel.

Report presenting the results of an experimental investigation of the pressure distribution over two triangular wings at supersonic speeds. The two wings which were tested had identical plan forms, 45 degrees of sweepback of the leading edge, and an aspect ratio of 4.0, but different airfoil sections. Results regarding the pressure distribution at zero lift, flow characteristics and pressure distribution at angles of attack, normal-force coefficients, and application of results to other triangular wings are provided.

Report presenting an investigation to determine the effects of magnitude and circumferential extent of inlet total-pressure distortions on the overall an component performance of a current turbojet engine. Results regarding the pressure and temperature profiles, component performance, engine pumping characteristics, net thrust and net-thrust specific fuel consumption are provided.

"An investigation of the altitude performance characteristics of an Allison J35-A-17 turbojet engines have been conducted in an altitude chamber at the NACA Lewis laboratory. Engine performance was obtained over a range of altitudes from 20,000 to 60,000 feet at a flight Mach number of 0.62 and a range of flight Mach numbers from 0.42 to 1.22 at an altitude of 30,000 feet. The performance of the engine over the range investigated could be generalized up to an altitude of 30,000 feet" (p. 1).