"Results of a static stability controls investigation carried out with a very low-aspect-ratio delta-winged missile are presented. Control effectiveness comparisons are made for tail, canard, and nose control configurations with respect to angle of attack, angle of bank, and Mach number. Trim capabilities of the various configurations are also presented" (p. 1).

Memorandum presenting heat-transfer rates and pressure fluctuations at Mach numbers of 1.98 and 4.95 measured at the stagnation point of a concave hemisphere for a range of Reynolds numbers based on free-stream conditions and model diameter. Results regarding heat-transfer characteristics, heat-transfer data, and schileren photographs and stagnation point pressure measurements are provided.

From Introduction: "A comparison is also made of the actual performance of two contemporary jet engines with estimated performance, assuming the engines were equipped with adjustable-angle stators and adjustable exhaust nozzles. Charts are presented that aid in estimating the performance of adjustable-stator turbines."

A comparison of available results from heat-transfer investigations on cascades of turbine blades is presented using the Nusselt equation. The conventional correlation procedure is modified by defining the Reynolds number by the average of the velocities and the pressures around the blades. The correlation of the results from impulse blades was improved by using the Reynolds number defined by the average velocity and pressure. The final comparison indicated that several variables, which possibly influence heat transfer, should be investigated.

Report presenting a program to determine limiting values of the aerodynamic parameters used in turbine design, which includes a study of several turbine designs suitable for application in current aircraft power plants. In this first report, the performance of a single-stage turbine of conservative design was studied for the purpose of establishing a basis for the comparison of turbine performance of less conservative designs.

Memorandum presenting an investigation of internal film cooling of the combustion chamber of a 1000-pound-thrust liquid-ammonia-liquid-oxygen rocket engine. The three coolants studied were water, ethyl alcohol, and liquid ammonia. Results regarding heat-transfer results, liquid film-cooled length, correlation of heat-transfer data, and effect of film cooling on performance are provided.

Report presenting a wind-tunnel investigation to evaluate the effects of Mach and Reynolds number on the characteristics of the internal and external flow about an E-type cowling suitable for a turbine-propeller power-plant installation. Results regarding the pressure-coefficient distributions, critical Mach number, cowl-gap flow, ham recovery, and wake-survey drag are provided.

Memorandum presenting a summary of the methods for estimation of water landing loads on hydro-ski-equipped aircraft in order to provide a unified picture and bibliography of NACA work on the subject. Two approaches to the problem of calculating hydro-ski landing loads are covered. Results regarding the impact load theory for rigidly mounted hydro-skis, effect of chine immersion on landing loads, impact load theory for shock-mounted hydro-skis, and estimation of the water pressure distribution on impacting hydro-skis are provided.

Report presenting an outline of a proposed statistical program to collect data for the establishment of more realistic maneuver-loads design criteria. Some sample experimental data are also included to indicate possible methods of statistical analysis and the potential sample size needed for the program.

Report presenting an investigation in the high speed tunnel of some effects of wing height and angle of attack on the vertical-tail pressure distribution of a complete model in sideslip at high subsonic speeds. The 45 degree swept wing had an aspect ratio of 4, a taper ratio of 0.30, and NACA 65A006 airfoil sections parallel to the model plane of symmetry. Results regarding vertical-tail loads and vertical-tail center of pressure are provided.

Memorandum presenting an investigation of reaction controls that command velocity and attitude that compares them to the controls that command acceleration. Proportional acceleration reaction controls were found to be satisfactory over a much wide range of control effectiveness than were the on-off acceleration controls. The velocity and attitude controls were found to be superior to either of the acceleration controls.

"At the request of the Air Materiel Command, Army Air Forces, an investigation is being conducted at the NACA Cleveland laboratory to determine the performance characteristics of the XJ-41-V turbojet-engine compressor. The static-pressure variation in the direction of flow through the compressor was presented in reference 1 for an equivalent speed of 8000 rpm. An analysis of these pressure indicated that the maximum-flow limitation of the compressor was caused by separation, which reduced the effective flow area at the vaned-collector entrance" (p. 1).