Engine dynamics and controls data are presented for a ram-jet engine which was operated in a free-jet facility at a Mach number of 2.76 and altitudes from 68,000 to 82,000 feet. The predominant engine dynamic characteristics was dead time, with values ranging from 0.018 to 0.053 sec. The control systems were designed to hold a constant ratio of a diffuser static pressure to an inlet-cone reference static pressure.

For a given wing and supersonic Mach number, the problem of shaping an adjoining fuselage so that the combination will have a low wave drag is considered. Only fuselages that can be simulated by singularities (multipoles) distributed along the body axis are studied. However, the optimum variations of such singularities are completely specified in terms of the given wing geometry. An application is made to an elliptic wing having a biconvex section, a thickness-chord ratio equal to 0.05 at the root, and an aspect ratio equal to 3. A comparison of the theoretical results with a wind-tunnel experiment is also presented.

Report discussing testing to determine the static lateral and directional stability and control characteristics of a model of the Republic F-105 airplane. The effects of various vertical tails and ventral fins, wing-tip fences, a canopy fin, fuselage nose shape, external stores, and deflection of horizontal tail, spoiler, and rudder were explored.

Report describing an experiment to obtain heat-transfer and pressure-drop data for the air side of a liquid-metal to air, shell-and-tube heat exchanger. Testing was conducted in a 500 kilowatt facility using sodium as the shell-side heating fluid. Results regarding the shell-and-tube heat exchanger and finned-tube heat exchanger friction factor are provided.

Experimental investigation of engine dynamics and controls for 48-inch ramjet engine in free jet facility at Mach number 2.76 and altitudes 68,000 to 82,000 feet. The engine data presented include steady-state performance, indical response, frequency response, and ignition characteristics. Ignition data are presented for representative fuel-air ratios which show that the normal shock overshoots its final position by several feet during ignition transients.

Report presenting an experimental investigation of a modified parabolic-bladed centrifugal impeller that was altered by cutting back every other blade to form splitter vanes. It was investigated over a range of equivalent impeller tip speeds and a range of flow rates. Results regarding the overall performance characteristics, a comparison of the splitter vane impeller and the fully bladed impeller, the maximum weight flow, and static-pressure ratios are provided.

Report presenting an investigation using the transonic-bump technique of some effects of sweep and thickness on the transonic downwash and wake characteristics of a series of highly tapered semispan wings with an aspect ratio of 3. Results regarding the downwash characteristics and wake characteristics are provided.

From Summary: "Data from ditching investigations conducted at the Langley Aeronautical Laboratory with dynamic scale models of various airplanes are presented in the form of tables. The effects of design parameters on the ditching characteristics of airplanes, based on scale-model investigations and on reports of full-scale ditchings, are discussed. Various ditching aids are also discussed as a means of improving ditching behavior."

From Summary: "Several methods of obtaining the time response of Linear systems to either a unit impulse or an arbitrary input from frequency-response data are described and compared. Comparisons indicate that all the methods give good accuracy when applied to a second-order system; the main difference is the required computing time. The methods generally classified as inverse Laplace transform methods were found to be most effective in determining the response to a unit impulse from frequency-response data of higher order systems. Some discussion and examples are given of the use of such methods as flight-data-analysis techniques in predicting loads and motions of a flexible aircraft on the basis of simple calculations when the aircraft frequency response is known."

Report presenting an investigation of the boundary-layer characteristics at the mean radius immediately downstream of a typical turbine stator blade over a range of blade-outlet critical-velocity ratio from 0.8 to 1.16. Total boundary-layer momentum thickness for the blade and individual thicknesses obtained for the suction and pressure surfaces are compared with values calculated from the turbulent-boundary-layer theory.