From Introduction: "The purpose of this analysis was to investigate the use of a function of intake-manifold pressure, exhaust back pressure, intake manifold temperature, and engine speed in place of a venturi as a means of measuring engine air consumption and to determine if this function is suitable for automatic mixture control."

"An investigation has been conducted in the Langley 20-foot free- spinning tunnel scale model of the Cornelius XFG-1 glider, a tailless design having its wings swept forward 15 degrees. It was previously found to possess erratic spin and recovery characteristics, and tests were made to determine modifications which would lead to normal steady spins with consistently good recoveries. The results of the investigation indicated that modifications that aid not appreciably alter the basic design aid not appreciably improve the spin and recovery characteristics" (p. 1).

Report presenting an investigation of the closed wind-tunnel phenomenon of choking and the wall-constriction effects in the subsonic Mach number range where supersonic Mach numbers appear using the hydraulic analogy. Application of the results to wind tunnel testing, the subsonic choking phenomena, and effects of the walls are described.

Report presenting the results of an experimental investigation of rim cracking in a welded-blade composite gas-turbine wheel, in two carbon-steel disks, and five tool-steel disks. Various characteristics were investigated, including the effectiveness of holes in preventing crack propagation and the influence of hardness and various types of notch on rim cracking.

Memorandum presenting an investigation conducted to evaluate the effectiveness of a simple internal regenerative fuel preheater for a 20-inch-diameter ram jet. Data obtained at subsonic sea-level conditions indicated that fuel could be successfully preheated in this manner.

Report presenting testing of a model of a Navy Bureau of Aeronautics design in Langley tank no. 2 to determine the calm-water take-off and rough-water landing characteristics of the design with particular attention paid to the take-off resistance and landing accelerations. Results regarding resistance, take-off stability, landing stability, spray, and landing acceleration are provided.

Report presenting a flight investigation to determine horizontal-tail loads at transonic speeds of the Bell X-1. The tests were made through the transonic region and at high lift coefficients. Results regarding the time histories, tail load data, aerodynamic-center positions, and potential load discrepancy explanations are presented.

Report presenting an investigation to determine the low-speed yaw characteristics of an airplane model with a 47.7 degree sweptback wing of aspect ratio 6 and to determine lateral stability contributions of various model components and associated mutual interference. The complete airplane model was directionally stable through the yaw-angle range for angles of attack up to 23 degrees.

Report presenting information about airfoil section normal-force, drag, pitching-moment, flap-normal-force, and hinge-moment characteristics at Mach numbers from 0.5 to 1.0 on an NACA 64A006 airfoil with 15-percent-chord leading-edge flap. Differing results were noted in the Mach ranges of 0.5 to 0.8 and over 0.8.

From Introduction: "The development of this air-borne optical target simulator and the results of evaluation flight tests (including a comparison of airplane tracking performance against the simulated and an actual target airplane) are presented herein."

Memorandum presenting an investigation to determine the nature of the pressure distribution and the order of magnitude of the pressures on a streamline body moving on a water surface. The body of revolution was equipped with chine strips and had a fineness ratio of 9. The results from the investigation indicate that there is a characteristic pattern of hydrodynamic pressure distribution for streamline bodies equipped with chine strips and moving on a water surface.

Memorandum presenting an investigation to determine the static longitudinal stability contribution of a horizontal tail at two vertical locations behind a 4-percent-thick unswept-wing-fuselage combination at transonic speeds. The model used in tests is comprised of an unswept wing located in the midwing position on a body of revolution and a sweptback horizontal tail mounted on a vertical tail.

Report presenting an investigation in the stability tunnel at low speed to determine the rolling characteristics at combined angles of attack and sideslip for a model of a fighter-type airplane with a 45 degree sweptback wing. Testing was performed with the original vertical tail and a vertical tail with a 27 percent larger exposed area. Results regarding the static longitudinal stability, directional stability, and effect of the different tails are presented.