From Summary: "A brief investigation was conducted in the altitude wind tunnel to determine the extent to which the afterburner shell cooling problem could be alleviated by internal configuration changes. Data were obtained with and without a cooling liner installed and for variations in the radial fuel distribution and in the radial distribution in flame-seat area. Consideration is given to the effects on both shell temperature and afterburner performance."

Memorandum presenting calculations made to determine the deceleration at any time after jettisoning of an airplane nose-section design typical of those which have been proposed as escape devices for high-speed airplanes. The decelerations were determined by two methods, one using successive approximations requiring graphical integration and the other giving reasonably close approximations by direct computation.

Report presenting an investigation at a Mach number of 1.24 using the NACA wing-flow method to determine the longitudinal-control effectiveness and downwash characteristics of a scale semispan model of the variable-sweep Bell X-5 airplane with the wind swept back at several different degrees. Lift, drag, and pitching moments were obtained for various angles of attack for several horizontal tail settings and with the tail off for each angle of sweep of the wing.

Report presenting an investigation of the altitude operational characteristics of a prototype model of the J47D turbojet engines, which includes an afterburner, a variable-area exhaust nozzle, and an integrated electronic control in an altitude wind tunnel. Results regarding compressor stall, compressor unstall, combustor blow-out during acceleration, stall and blow-out protection, acceleration characteristics, deceleration characteristics, and altitude starting characteristics, afterburner operational characteristics are provided.

Report presenting the effect of preinjection-fuel temperature on vaporization rates and combustion efficiency of a 16-inch ram-jet engine for two different fuels. Variation of the location of the fuel injectors and use of control sleeves were also explored.

Information concerning the parameters and design variables affecting an NACA submerged duct design is presented.

From Summary: "Qualitative investigations have shown that use of the NACA injection impeller with the R-3350 engine increases the inertia of the fuel-injection system and, when the standard fuel-metering system is used, this increase in inertia results in poor engine acceleration characteristics. This investigation was therefore undertaken to determine whether satisfactory acceleration characteristics of the engine equipped with the injection impeller could be obtained by simple modifications to the fuel-monitoring system. The engine was operated with two types of carburetor; namely, a hydraulic-metering carburetor incorporating a vacuum-operated accelerating pump and a direct-metering carburetor having a throttle-actuated accelerating pump."

Report presenting an investigation of a 15 degree semiangle movable-cone variable-geometry ram-jet inlet to determine the variable-geometry effect on total-pressure recovery at free-jet Mach numbers of 1.62, 2.00, 2.53, and 3.05 at zero angles of attack and yaw. Generally, increasing the cowling-position parameter increased the value of both total-pressure recovery and mass-flow ratio. Results regarding the total-pressure recovery, shadowgraphs, and total-pressure recovery as a function of free-stream Mach number are provided.

"The purpose of this investigation was to obtain information for use in the design of truss and plywood forms, particularly with reference to wing ribs. Tests were made on many designs of wing ribs, comparing different types in various sizes. Many tests were also made on parallel-chord specimens of truss and plywood forms in place of the actual ribs and on parts of wing ribs, such as truss diagonals and sections of cap strips" (p. 223).

"The hot-wire anemometer suggests itself as a promising method for measuring the fluctuating air velocities found in turbulent flow. The only obstacle is the presence of a lag due to the limited energy input which makes even a fairly small wire incapable of following rapid fluctuations with accuracy. This paper gives the theory of the lag and describes an experimental arrangement for compensating for the lag for frequencies up to 100 or more per second when the amplitude of the fluctuation is not too great. An experimental test of the accuracy of compensation and some results obtained with the apparatus in a wind-tunnel air stream are described. While the apparatus is very bulky in its present form, it is believed possible to develop a more portable arrangement" (p. 359).

"A 1/13-scale Republic F-105 wing-root inlet configuration in which inlet components were varied was tested in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1,41, 1.81, and 2,01 corresponding to Reynolds numbers per foot of 4,19 X 10(exp 6) , 3.74 X 10(exp 6) , and 3.46 x 10(exp 6) respectively. Angles of attack ranged from -4 deg to 15 deg and a few configurations were tested in a sideslip range from -8 deg to 4 deg. Inlet performance and engine-face flow distortions as affected by pitch, sideslip, inlet-lip sweep, contraction ratio, boundary-layer control, and engine bypass are presented and discussed" (p. 1).