Memorandum presenting an investigation of the effectiveness of water-vaporization cooling that would be obtained by ejecting water upstream from the stagnation point conducted in a liquid-fuel rocket jet as a stagnation temperature of 4000 degrees Fahrenheit.

Report presenting an investigation in the altitude test chamber to evaluate several afterburner configurations on the XJ79 engine. Data were obtained from nine configurations which show the effect on burner performance of increased burner diameter and modifications to the flameholder, fuel system, and flow swirl.

Report presenting an investigation in the transonic blowdown tunnel to determine the effects of inlet-lip sweep angle on the internal-flow characteristics of a semielliptical scoop-type inlet with an inlet lip stagger of 30 degrees. the testing was performed at a range of Mach numbers and mass-flow ratios. Results regarding flow over the nose, total-pressure recovery at inlet, flow distortions at inlet, boundary-layer control, and inlet performance are presented.

One-dimensional mean-section flow and blade specific losses proportional to average specific kinetic energy are assumed in the analysis. Range of the work-speed parameter lambda considered includes low to moderate blade speeds with high specific work outputs, where critical turbojet, turbopump, and accessory-drive turbines are encountered. A diffusion factor of 0.5 limits the loading on the downstream stators. Turbine efficiences considered are total or aerodynamic, rating, and static. Efficiences of velocity-diagram types at impulse and that corresponding to values of maximum efficiency are presented and compared to indicate in what range of lambda downstream stators are beneficial as well as the attending improvements in efficiency.

Report presenting a sample of data on atmospheric turbulence on Lockheed U-2 airplanes during research flights. The intensity, amount, and extent of atmospheric turbulence observed in the United States is in good agreement with data from England and Western Europe. Results regarding overall gust distribution, intensity of turbulence, percent of rough air, and size of turbulent areas are provided.

"A convenient summary is given of useful formulas on the kinematics of high energy electron scattering together with a derivation of the relevant formulas for transforming from the center of mass to the laboratory system such parameters as scattering cross sections. The formulas derived hold for any two- body collision: the approximation (m = 0) employed for the electron scattering calculations is rigorously true for the elastic scattering of photons."

At the request of the Alloy Preparation Group, the Nondestructive Test Development Group investigated the feasibility of determining the clad thickness on Mark X MTR Fuel Plates. As the use of induced eddy-currents was considered to be the most promising approach, a prototype instrument and probe coil utilizing this principle was developed to measure clad thickness. The results of the investigation conducted with this instrument indicate that the clad thickness of this type of fuel plats can be measured to withing +- 0.001 in.