Report presenting the results of an investigation in the full-scale tunnel of the static longitudinal stability and control of a convertible-type airplane as affected by articulated- and rigid-propeller operation. The investigation included force measurements for a large angle-of-attack range with the all-movable horizontal tail installed and removed.

Report presenting an analysis of a number of free-flight transient responses resulting from small stabilizer movements obtained during testing of the Bell X-1 airplane to obtain its longitudinal stability characteristics. A comparison of flight data and model test data is also provided.

Report presenting an investigation of three air inlets designed for use at transonic speeds conducted in the 8-foot high-speed tunnel. The basis of the design of the inlets was the use of a nose which was shaped so that substream velocities are maintained on its surface for high-speed operating conditions. Results regarding impact pressure recovery, external pressure distributions, wake-survey drag, supersonic external pressure drag, and design considerations are provided.

Report presenting an investigation in Langley tank no. 2 to determine the hydrodynamic characteristics of the Consolidated Vultee Skate 7 seaplane with twin hydro-skis suitable for use on water or snow. Results regarding the take-off stability in smooth and rough water, landing stability, spray characteristics, and resistance are provided.

"Turbine-outlet radial temperature distributions of an XJ34-WE-32 turbojet engine were investigated in the altitude wind tunnel at the NACA Lewis laboratory over a range of pressure altitudes, engine-inlet air temperatures and flight Mach numbers at or near rated engine conditions. From blade stress considerations, the turbine-outlet temperature distribution was considered satisfactory at altitudes up to 25,000 feet at corrected engine speeds corresponding to rated speed (12,500 rpm); however, operation at either higher corrected engine speeds or higher altitudes resulted in an inversion of the turbine temperature distribution that was detrimental to turbine life. Installation of a compressor-outlet mixer greatly improved the turbine radial temperature distribution" (p. 1).

"An investigation was conducted at the NACA Lewis laboratory to obtain pressure-drop data for flow of air with no heat addition through mockups of two reactor segments of the proposed General Electric Company aircraft reactor. Pressure-drop data were obtained over a range of Reynolds numbers from 4000 to 80,000, air inlet Mach numbers from 0.02 to 0.40, inlet pressures up to about 40 inches of mercury absolute, and ambient air temperatures. factors, corrected for entrance, vena contracta, momentum, and exit losses, are considerably higher at the high Reynolds numbers than those reported for turbulent flow in smooth pipes" (p. 1).

Memorandum presenting an investigation in the Lewis laboratory to obtain pressure-drop data for flow of air with no heat addition through mockups of two reactor segments of the proposed GE aircraft reactor. Pressure-drop data were obtained over a range of Reynolds numbers, air inlet Mach numbers, inlet pressure, and ambient air temperatures. The results indicate that the friction factors, corrected for entrance, vena contracta, momentum, and exit losses are considerably higher at high Reynolds number than those reported for turbulent flow in smooth pipes.