From Introduction: "This report presents an analysis of the effect of variations in the work and requirements on the efficiency characteristics of single-stage, full-admission turbines."

Memorandum presenting component interference studies that have been made in an attempt to explain the unexpected large loss in damping in roll which occurred in wind-tunnel tests at zero angle of attack for the Bell X-1A research airplane near a Mach number of 2.22. The studies include theoretical calculations of the effect of the body flow field on the wing damping in roll and measurements at several Mach numbers on the contribution of the individual components to the damping in roll.

Report presenting an investigation of the release characteristics of dynamically scaled stores carried internally in a simulated bomb bay at Mach numbers of 1.39 and 1.98. A model of the Republic F-105 half-fuselage and bomb-bay configuration was tested with four store shapes: the MK-7 store, the bluff store, the TX-28 store, and turnabout TX-28 store. Results regarding ejection photographs and data plots are also provided.

Report presenting measurements of aerodynamic heat transfer at several stations on the 15 degree total angle conical nose of a rocket-propelled model in free flight at Mach numbers up to 5.2. Laminar, transitional, and turbulent heat-transfer coefficients are provided. Results regarding skin temperature time histories, transition, and computed skin temperatures are provided.

"A highly polished 15 degree included-angle cone-cylinder with hemispherical tip has been flown to obtain boundary-layer transition and heat-transfer data. The model was launched from a carrier plane at an altitude of 47,500 feet. Laminar flow existed at a Reynolds number greater than 38.5 x 10(exp) 6 on the cylinder when the model was at the peak free-stream Mach number of 8.17. The results indicate an appreciable and favorable effect of tip bluntness in raising the allowable skin temperature for a given boundary-layer transition Reynolds number" (p. 1).

Report presenting an investigation of the effect of reducing the static stability by a practical center-of-gravity shift in swept-wing airplanes of low aspect ratio with no horizontal tail. Results regarding relocating the center of gravity, the effect of lift due to elevator deflection, the effect of increased total elevator effectiveness, and the effect of response characteristics over long time periods are provided.

Report presenting two-dimensional aerodynamic lift and moment flutter derivatives for moderate and high angles of attack for several airfoil profiles varying in thickness and thickness distribution. The results indicate that the variables angle of attack, airfoil profile, reduced frequency, and Mach number all have significant interdependent effects.

Pressure recovery in adjustable supersonic inlet combined with J34 turbojet engine up to Mach 2.0.

Report presenting an investigation of an annular nose inlet equipped with a remotely controlled translating spike and variable bypass in the supersonic wind tunnel. The inlet performance was explored with the airflow controlled by an operating J34 engine and with the engine simulated by a choked plug. Results regarding the performance of the inlet, corrective action that should be applied to avoid pulsing, performance of the subsonic portion of the diffuser, supersonic performance, radial-flow profiles, and other flow profiles are provided.

Report presenting an investigation in the transonic tunnel to determine the effects of varying Reynolds number on the pressure distribution on a transonic body of revolution at angles of attack through the transonic speed range. The effect of change in sting cone angle on the pressure distributions and a comparison of experimental incremental pressures with theory is also provided.

From Summary: "From a theory developed on a quasi-one-dimensional-flow basis, it was found that the stability of the ram jet is dependent upon the instantaneous values of mass flow and total pressure recovery of the supersonic diffuser and immediate neighboring subsonic diffuser. Conditions for stable and unstable flow were presented. The theory developed in the report was in agreement with the experimental data of the reports both of Sterbentz and Evvard and of Ferri and Nucci."

From Summary: "A 1/4-scale dynamically similar model of the XFV-1 airplane has been flown in the Ames 40- by 80-foot wind tunnel, using the trailing flight-cable technique. This investigation was devoted to establishing the flight characteristics of the model in forward flight from hovering to wing stall, and in yawed flight (wing span alined with the relative wind) from hovering to the maximum speed at which controlled flight could be maintained. Landings, take-offs, and hovering characteristics in flights close to the ground were also investigated."

Report discussing the drag and pressure recovery of a model with a nose inlet with a parabolic arc at zero angle of attack. External drag coefficient and total-pressure recovery at the end of the diffuser were measured at a range of Mach numbers and mass-flow ratios.

The effectiveness of molybdenum disulfide MoS2 as a bearing lubricant was determined at high temperature and at high speeds. A 1-inch-bore ball bearing operated at temperatures to 1000 F, a speed of 1725 rpm, and a thrust load of 20 pounds when lubricated only with MoS2-air mist. A 75-millimeter-bore cageless roller bearing, provided with a MoS2-syrup coating before operation, operated at DN values to 1 x 10(exp 6) with a load of 368 pounds.

An investigation of the pressure distribution on the fuselage nose and the pilot canopy of a supersonic airplane model has been conducted at a Mach number of 1.90 over a wide range of angles of attack and yaw. Boundary layer separation apparently occurred from the upper surface at angles of attack above 24 degrees and from the lower surface at minus 15 degrees. No separation from the sides of the fuselage was evident at yaw angles up to 12 degrees.