Memorandum presenting an investigation made to valuate the effects of vertical height of the horizontal tail on the static longitudinal stability of a model with a wing with 35 degrees of sweepback, an aspect ratio of 4.5, a taper ratio of 0.5, and NACA 64A010 sections. The investigation also included the effects of adding a partial-span, leading-edge chord extension to the outer portions of the wing. Results regarding the effect of tail height, wing-wake and local downwash measurements, and effect of a leading-edge extension are provided.

Thesis discussing "a technique for determining the generation times of individual yeast cells...the effect of x-radiation on the generation times of individual cells and their progeny..." and "attempts to synchronize cell division in a population of cells."

Memorandum presenting an investigation of an experimental tubular combustor that provides for prevaporizing and premixing of the fuel with a part of the air before its introduction into the combustion zone. Combustion efficiency and total-pressure loss data are presented for three configurations selected from a total of 43 different modifications investigated. Results regarding the combustor development, comparison of liquid and gaseous fuel, combustor total-pressure losses, combustor-outlet temperature distribution, and evaluation of experimental prevaporizing combustors are provided.

From Introduction: "The over-all altitude-performance characteristics of this engine are reported herein, and the component performance characteristics are given in reference 1. The data are presented in the form of engine pumping characteristics to allow accurate calculation of engine performance at any operating or flight condition within the range covered by the experimental data. A curve is also presented that will allow determination of thrust in flight by the measurement of ambient static pressure and total pressure in the exhaust nozzle."

Report presenting an investigation to determine the altitude performance characteristics of a J73-GE-1A turbojet engine conducted in an altitude chamber. The engine had a ten-percent oversize turbine-nozzle are compared with the production J73 engine. Results regarding radial pressure and temperature profiles, compressor performance, combustor performance, turbine performance, and tail-pipe-diffuser and exhaust-nozzle performance.

Report presenting an experimental investigation to determine the performance of seven full-size ejector configurations over a range of secondary to primary air-flow ratios, primary total- to ambient-pressure ratios, and primary gas temperatures. Results regarding primary-nozzle performance, ejector performance, typical ejector characteristics, effect of operating temperatures on ejector flow characteristics, and effect of geometry on ejector performance are provided.

Report presenting theoretical performance characteristics and estimates of effective specific impulse and weight for rocket engines serving a main and booster power plants for missiles. The fuels used included ammonia-fluorine and JP4-oxygen propellants. At extremely high altitudes, the specific impulse depends primarily on the expansion ratio.

Report presenting flight testing of a 60 degree delta wing (NACA 65A003 airfoil section) mounted in midwing and high-wing positions on a modified transonic body from Mach numbers 0.8 to 2.0. The high-wing configuration without nacelles had higher drag coefficients than the midwing configuration without nacelles, but both configurations had approximately the same longitudinal distribution and frontal area. Results regarding nacelle internal drag, configuration drag, nacelle drag coefficient, and normal-force coefficient are provided.

From Introduction: "The self-shielding characteristics of a number of absorbers and of U-235 and U-238 have been investigated in PPA-20 (66°). Most of the measurements have been made in Ring 3 at the core mid-plane. The foil doubling technique was employed. Particular attention was given to 'thin' foil regions for the purpose of extrapolating the data to zero thickness."

The following report is a general monthly progress report conducted by the radiation laboratory of the University of California discussing experimental physics, theoretical physics, the MTA target physics program, accelerator construction and operation, biology and medicine, and a plant and equipment report. The period being covered is January 15, 1954 to February 15, 1954.

The absorption bands induced in α-Al2O3 by gamma and reactor irradiation have been studied. The slight coloration due to γ-rays saturates. Bands specific to reactor irradiation have been found and their growth studied.

"The static lateral, directional, and longitudinal stability characteristics of a 0.06-scale model of the Martin B-61A missile (Matador) were investigated in the Langley 8-foot transonic tunnel at Mach numbers from 0.80 t o 1.12. Six-component force and moment data were obtained from strain-gage measurements. The characteristics of a spoiler and of wing-tip end plates were also investigated. The Reynolds number of the tests based on the mean aerodynamic chord of the wing was approximately 1.6 X 10(exp 6)" (p. 1).

An investigation of a method of preparing intricately shaped objects such as turbo-supercharger blades from refractory powders. The method consists of preparing an extremely thick slip of materials like titanium carbide with a small amount of binder, casting the slip in a mold, and freezing to retain the shape of the casting. Results regarding the applicability of the method and factors affecting soundness, are provided.

Report presenting an investigation to determine the low-speed chordwise pressure distributions near the midspan station of the slotted flap and aileron of a model of the Bell X-1 airplane with a wing of aspect ratio 4, taper ratio 0.5, 0 degree sweepback of the 40-percent-chord line, and a modified NACA 64A004 airfoil section. Results regarding section pressure distribution and section normal-force and pitching-moment coefficients are provided.

Memorandum presenting an investigation made of the effects of circular end plates on the aerodynamic characteristics of a modified triangular wing of aspect ratio 2 and taper ratio 0.33. The experimental results show that the addition of end plates produces so slight a difference in the total change in static longitudinal stability with Mach number in the range from 0.6 to 1.9 that no beneficial effects on the trim drag may be realized.

From Summary: "An experimental investigation was made to determine the permeability and strength characteristics of a number of sintered, porous, hollow turbine rotor blades and to determine the effectiveness of the blade fabrication method on permeability control. The test blades were fabricated by the American Electro Metal Corporation under a contract with the Office of Naval Research, Department of the Navy, and were submitted to the NACA for testing. Of the 22 test blades submitted, ten were sintered but not coined, five were sintered and coined, and seven were sintered and not coined but contained perforated reinforcements integral with the blade shells. Representative samples of each group of blades were tested."

"An investigation of a decoupler and a controlled-feathering device incorporated with the YT-56A turboprop engine has been made to determine the effectiveness of these devices in reducing the high negative thrust (drag) which accompanies power failure of this type of engine. Power failures were simulated by fuel cut-off, both without either device free to operate, and with each device free to operate singly. The investigation was made through an airspeed range from 50 to 230 mph" (p. 1).

Report presenting a method using charts for the systematic determination of a corrugation geometry configuration which, for a specific application to an air-cooled turbine blade, gives the required amount of blade temperature reduction using the minimum amount of coolant flow within pressure-drop limitations. A numerical example is included to illustrate the use of the method.

Report presenting an investigation conducted to determine the importance of the mixing loss downstream of a blade row with respect to blade profile loss for compressible flow conditions. Theoretical and experimental results and the application of mixing loss results to the example transonic turbine are provided.