"A complete stage of an axial-flow compressor was designed and built to investigate the possibility of obtaining a high pressure ratio with an acceptable efficiency through the use of the optimum combination of high blade loading and high relative inlet Mach number. Over-all stage performance was investigated over a range of flows at equivalent tip speeds of 418 to 836 feet per second. At design speed (836 ft/sec), a peak total-pressure ration of 1.445 was obtained with an adiabatic efficiency of 0.89. For design angle of attack at the mean radius, a total-pressure ratio of 1.392 was obtained" (p. 1).

An investigation of tail-pipe burning was conducted in the NACA Lewis altitude wind tunnel with a full-scale turbojet engine and an 29-inch-diameter tail-pipe burner. Effects of fuel distribution and number and arrangement of stages on performance and operational characteristics of several fuel-cooled flame holders are presented and discussed. Operation with a three-stage flame holder having the large stage upstream was the most efficient. Combustion efficiency was slightly increased at high altitudes by injecting fuel upstream of the flame holder.

"At the request of the Air Materiel Command, an investigation was made in the Langley free-flight tunnel to determine the longitudinal stability and control characteristics of models coupled together in a tandem configuration for aerial refueling similar to one proposed by the Douglas Aircraft Company, Inc. Static force tests were made with 1/20-scale models of the B-29 and F-80 airplanes to determine the effects of rigidly coupling the airplanes together. The Douglas configuration differs from the rigid configuration tested in that it provides for some freedom in pitch and vertical displacement" (p. 1).

Performance of four 16-inch-diameter ram-jet units was determined at free-stream Mach numbers of 0.49 to 1.78 over range of gas total-temperature ratios of 1.0 to 6.1. Time histories of each flight and data on thrust, drag, diffuser efficiency, and combustion are presented. A maximum thrust coefficient of 0.88 and a maximum net acceleration of 5.13 g's were observed for the four units.

Report presenting measurements of the buffet boundary and peak normal-force coefficients for the Douglas D-558-II airplane up to a Mach number of 0.90. Results regarding airplane lift curves and a comparison between the maximum normal-force coefficients and buffet boundaries for this particular aircraft and the Bell X-1 airplane are also provided.

The flame velocities of 37 pure hydrocarbons including normal and branched alkanes, alkenes, and alkynes; as well as benzene and cyclohexane, together with the experimental technique employed are presented. The normal alkanes have about the same flame velocity from ethane through heptane with methane being about 16 percent lower. Unsaturation increases the flame velocity in the order of alkanes, alkenes, and alkynes. Branching reduces the flame velocity.

Report presenting tests of a wing-body combination using the free-fall method, which was made up of a fineness-ratio-12 body with a 45 degree sweptback wing, an aspect ratio of 3.75, and an NACA 65-003 airfoil section in the direction perpendicular to the 50-percent-chord line. Results regarding the complete configuration, wing, body-tail combination, and component effects on total drag are provided.

"A 30-inch tip-diameter axial-flow compressor stage was investigated with and without rotor to determine individual blade-row performance, interblade-row effects, and outer-wall boundary-layer conditions. Velocity gradients at guide-vane outlet without rotor approximated design assumptions, when the measured variation of leaving angle was considered. With rotor in operation, Mach number and rotor-blade effects changed flow distribution leaving guide vanes and invalidated design assumption of radial equilibrium" (p. 1).

An investigation was made of the spray characteristics of a jet-powered dynamic model of the Bureau of Aeronautics DR 56 flying-boat design with a vee tail. A limited investigation was made to determine the effect of the change in tail design on the take-off and landing behavior in smooth water and in waves 8 feet high (full size).

Report presenting an experimental investigation to determine the combustion properties of aluminum as a fuel for use in high-speed aircraft. The aluminum fuel was injected both in powder and wire form into 2-inch-diameter ramjet-type combustors. Results regarding operational problems, thrust, and combustion efficiency are provided.

Report presenting testing conducted to determine the force and pressure-recovery characteristics of a model utilizing a single-shock spike-type inlet with a perforated cowl. The use of the cowl resulted in the attainment of a high pressure recovery at zero angle of attack, but it was accompanied by a relatively large increase in external drag as compared with nonperforated inlets of the same proportions. Results regarding the characteristics at zero angle of attack, effects of changes in angle of attack and Mach number, and performance of perforations are provided.

From Wing Thickness: "A brief review of the effect of wing thickness and thickness distribution on the high-speed performance and stability characteristics of a representative configuration is presented."

Report presenting an investigation conducted at low speed of an air-induction system with twin scoop-type inlets on the sides of the fuselage of a model of an airplane designed for flight at supersonic Mach numbers. The leading edge of the lip of the scoop was rounded and there were provisions for control of the boundary layer ahead of the inlet. Results regarding the characteristics of the lips investigated, characteristics of the main duct with lip E, characteristics of the boundary layer control duct, and pressure coefficient distributions and boundary-layer characteristics are provided.

Total-pressure deficiency for an annular cascade of 65-(12)10 blades was measured at three radial stations over a range of Reynolds numbers from 50,000 to 250,000 and at angles of attack of 15 degrees and 25 degrees. The variation of turning angle and shape of static pressure distribution at these stations is also shown.

"A comparison of the operating characteristics of 75-millimeter-bore (size 215) cylindrical-roller one-piece inner-race-riding cage-type bearings was made using a laboratory test rig and a turbojet engine. Cooling correlation parameters were determined by means of dimensional analysis, and the generalized results for both the inner- and outer-race bearing operating temperatures are compared for the laboratory test rig and the turbojet engine. Inner- and outer-race cooling-correlation curves were obtained for the turbojet-engine turbine-roller bearing with the same inner- and outer-race correlation parameters and exponents as those determined for the laboratory test-rig bearing" (p. 1).

A preliminary investigation was conducted in quiescent air on a translating cowl technique for improving the take-off performance of a sharp-lip supersonic diffuser. The technique consists of cutting the cowling in a plane normal to its axis and then translating the forepart of the cowling in the forward direction. The leading edge of the fixed portion of the cowling is rounded. Appreciable improved inlet performance was obtained with a cowling translation corresponding to a gap of only 1/4 inlet radius.

"The drag and pressure recovery of an NACA submerged-inlet model and an NACA series I nose-inlet model were investigated in the transonic flight range. The tests were conducted over a mass-flow-ratio range of 0.4 to 0.8 and a Mach number range of about 0.8 to 1.10 employing large-scale recoverable free-fall models. The results indicate that the Mach number of drag divergence of the inlet models was about the same as that of a basic model without inlets" (p. 1).

Memorandum presenting a concept in aircraft design, which states that provision of a rolling moment in the direction of the turning rotation will be very effective, and may be necessary, for termination of any spin obtained. Current research indicates that wing sweep, use of heavy jet and rocket engines, in the fuselage, and long fuselage nose lengths are the primary causes of the changes in the nature of the spin and in the requirements for recovery.

Report discussing some new requirements for satisfactory handling qualities due to the drastic changes in the speed range and configuration of airplanes. Longitudinal characteristics, lateral and directional stability and control characteristics, dynamic lateral and directional stability, and control effectiveness are described. Four categories of characteristics that may affect pilot control are included and ranked by level of severity.

The dynamic characteristics of turbojet engine with variable exhaust nozzle area were investigated over a range of altitudes and flight Mach numbers. These characteristics generalize to standard static level condition. Data resulting from approximate step disturbances in either manipulated variable suggested functional relationships from which functions can be derived. The constants of the transfer functions are listed for five combinations of engine speed and exhaust nozzle area. The minimum data needed to completely define the transfer functions were: experimentally determined dynamic characteristics, such as engine time constant and initial rise ratio, resulting from either manipulated variable; static characteristics determined from steady-state performance curves.

Report presenting the low-speed longitudinal stability characteristics of a wing with 45 degrees of sweepback of the quarter-chord line, an aspect ratio of 8, a taper ratio of 0.45, and NACA 63(sub 1)A012 airfoil sections parallel to the air streams investigated in the 19-foot pressure tunnel. Results regarding the basic wing, wing with fences, wing with trailing-edge flaps, wing with leading-edge flaps, a combination of both flaps, fences with the flaps deflected, leading-edge roughness, and the wing-fuselage combustion are provided.

Report presenting an investigation of the aerodynamic interference effects associated with a missile configuration, consisting of a pointed body of revolution with one or two ramjet engines strut-mounted in a vertical plane through the center line of the body, at several engine locations relative to the body and a range of angles of attack. The experimental data indicated increases in slope of the normal force curve with outward movement of the engines. Results regarding the characteristics of isolated components, characteristics of representative configurations, interference effects, and effect of engine location on lift-drag ratio are provided.

Memorandum presenting an investigation conducted to explore the characteristics of metal-hydrocarbon combustion, to determine the effect of fuel-air ratio on the combustion efficiency, and to determine how the metal and hydrocarbon separately contribute to the overall combustion of several slurries. Results regarding an evaluation of the sampling method, combustion efficiency, effective metal weight fraction, effective hydrogen-carbon ratio, and heat of combustion per pound of air are provided.

Memorandum presenting a 10-stage axial-flow compressor designed for use as a research unit in which the problems associated with the compounding of high performance stages could be studied. The overall performance characteristics of the compressor, as determined experimentally, are included.