An investigation was conducted at a Mach number of 1.91 to determine spanwise pressure distribution over a wing tip in a region influenced by a sharp subsonic leading edge swept back at 70 degrees. Except for pressure distribution on the top surface in the immediate vicinity of the subsonic leading edge, the maximum difference between linearized theory and experimental data was 2 1/2 percent (of free-stream dynamic pressure) for angles of attack up to 4 degrees and 7 percent for angles of attack up to 8 degrees. Pressures on the top surface nearest the subsonic edge indicated local expansions beyond values predicted by linearized theory.

Memorandum presenting the low-speed lateral-control characteristics of a 37 degree sweptback semispan wing of aspect ratio 6 and NACA 64-series airfoil sections in the 19-foot pressure tunnel. The investigation included the measurement of the hinge-moment characteristics of an aileron and the rolling-effectiveness characteristics of the aileron and two configurations of spoilers.

Report presenting an investigation of the hypersonic similarity law for steady flow about bodies of revolution by correlating the forces and moments from tests at a range of Mach numbers and angles of attack. The data for the lifting cones and ogives are correlated by the hypersonic similarity law. Results regarding the similitude for lift and pitching moment and similitude for drag are provided.

From Summary: "The performance of an experimental annular turbojet combustor was investigated at a low-pressure operating condition with an uncoated liner, with an identical liner having a ceramic coating on the inner walls, and with this same liner having a catalytic coating added onto the ceramic coating. The combustion efficiency was approximately the same for all three liners, thus indicating no gain in performance through the use of the catalytic coating."

Report presenting the results of an investigation showing the effect of the variation of taper ratio on the lift, drag, and pitching-moment characteristics of thin wings of aspect ratio 3 with 53.1 degrees of sweepback of the leading edge. Three wings with three different taper ratios in combination with a high-fineness-ratio body were studied.

Report presenting an investigation to determine the effect of both six- and eight-blade dual-rotation propellers on the internal-flow characteristics of an NACA 1-series D-type cowl and the effect of the cowl on the characteristics of the propellers.

From Summary: "Flight tests of a P-51H airplane with two different vertical-tail assemblies were made to determine lateral and directional stability and control characteristics. The airplane had satisfactory directional stability in the landing, approach, and wave-off conditions with either tail. In the power-on clean and glide conditions, however, the airplane had weak directional stability with the original tail. The production tail, which had a 7-inch fin extension and a shorter span rudder, improved the directional stability in the power-on clean and glide conditions, but the stability was still weak in the power-on clean condition."

From Summary: "The tumbling characteristics of a 1/20-scale model of the Northrop N-9M airplane have been determined in the Langley 20-foot free-spinning tunnel for various configurations and loading conditions of the model. The investigation included tests to determine whether recovery from a tumble could be effected by the use of parachutes. An estimation of the forces due to acceleration acting on the pilot during a tumble was made. The tests were performed at an equivalent test altitude of 15,000 feet."