Memorandum presenting characteristics of a hydraulic control as determined by analyzing transient data obtained with a turbojet engine operating in the altitude wind tunnel. The excellent overall performance of the speed control is attributed to the elimination of large lags in the control system, thereby permitting the use of relatively high loop gains while still maintaining satisfactory damping in transients. Some information regarding the frequency-response analysis of speed control, simulation of speed control, and acceleration control are provided.

Report presenting testing of the transonic longitudinal characteristics of a model of the McDonnell XF3H-1 airplane. The model had a center-of-gravity location of 28.5 percent of the mean aerodynamic chord and a stabilizer setting of -5.91 degrees relative to the wing chord plane with extensible rocket racks. Results regarding Reynolds number, rocket-rack program, flight time history, trim, lift, drag, longitudinal stability, directional stability, and inlet pressure recovery are provided.

Memorandum presenting a general treatment of compressible flow in ejectors with friction in the mixing tube included. A secondary object is to show the application of the flow theory to the calculation of the effect of ejector addition on thrust of jet-propelled airplanes and missiles. Results regarding the outline of methods of applying the general theory to some other problems and future explorations of ejector problems are provided.

Report presenting an investigation of the effects of a variation of Reynolds number on the forces, moments, and surface pressures on a semispan model of a wing with 35 degrees of sweepback, an aspect ratio of 5, a taper ratio of 0.7, and the NACA 65(sub 1)A012 section in planes parallel to the plane of symmetry.

Report presenting the results of a free-flight investigation to determine the drag of circular, finite-length cylinders for a range of Mach numbers. For supersonic speeds, the drag of circular cylinders was found to be largely independent of fineness ratio and Reynolds number.

Report presenting pressure distributions and Schileren photographs of the flow around a 10-percent-thick diamond airfoil at zero lift in two-dimensional closed, slotted, and open-throat tunnels. Results regarding the effect of slot area ratio and effect of slot spacing are provided.

Report presenting an investigation of the overall performance of a 20-inch-tip-diameter 10-stage compressor as the initial step to examine the problems encountered in an axial-flow compressor with a high pressure ratio per stage. The investigation was carried out over a range of weight flows and percentages of the design speed. Results regarding the part-speed efficiency, surge characteristics, overspeed characteristics, compressor discharge Mach number, and stage characteristics are provided.

A preliminary study of pitching-moment data on tapered wings indicated that excellent agreement with test data was obtained by locating the quarter-chord point of the average chord on the average quarter-chord point of the semispan. The study was therefore extended to include most of the available data on tapered-wing models tested by the NACA.

"The object of the research project described herein is to present the design basis for test apparatus to determine the heat-transfer and pressure-drop characteristics of white fuming nitric acid flowing in a heated tube section. The heat flux to the tube will be of the order of magnitude occurring in a regeneratively cooled rocket engine" (p. 1).

Report presenting specimens of five different root designs, proportioned in accordance with the design surveys, and specimens of a conventional fir-tree turbine root were fabricated from a titanium carbide cement bonded with nickel. Comparative strengths were determined by short-term tensile tests at 1200 degree Fahrenheit. Results regarding blade root evaluation and rotor-segment evaluation are provided.

From Summary: "Ignition delays of several propellant combinations obtained with a modified open-cup apparatus and with a small-scale rocket engine of approximately 50-pounds thrust were compared to study any correlations that might exist between the two methods of ignition-delay determination. The results were used in determining the relative utility of each apparatus."

Memorandum presenting the results of a test on the transonic longitudinal characteristics of a scale rocket model of the McDonnell XF3H-1 airplane. The model, flown with a center-of-gravity location of 28.5 percent of the mean aerodynamic chord and a stabilizer setting of -5.91 degrees relative to the wing chord plane, was equipped with extensible rocket racks. Results regarding the Reynolds number, rocket-rack program, flight time history, trim, lift, drag, longitudinal stability, directional stability, and inlet pressure recovery are provided.

Report presenting results from a limited investigation of the use of controls during service operational training with four fighter airplanes. The service pilots utilized the positive V-n envelope in performing their training missions but rarely approached the negative V-n envelope. Results regarding the operational V-n diagram for the F-86A, F-84G, F2H-2, and F-84G, design curves, maximum elevator rates, maximum aileron rates, rolling velocities, and control surface angles are provided.

Report presenting an investigation of the performance characteristics of a mixed-flow impeller (Model MFI-1B) in combination with a vaned diffuser. The results indicated that the peak pressure ratio and maximum efficiency were not being obtained at overdesign speeds because of premature surge. Increasing inlet angle at the leading edge of the vanes improved the pressure ratio and efficiency at overdesign speeds with little to no effect on underdesign speeds.

Report presenting an experimental investigation in a 16-inch ram-jet engine to examine the degree to which inlet flow pulsations influence the combustion efficiency and lean blow-out limit of a ram-jet combustor.

"Experimental measurements of the attenuation of plane shock waves moving over rough walls have been made in a shock tube. Measurements of the boundary-layer characteristics, including thickness and velocity distribution behind the shock, have also been made with the aid of new cal techniques which provide direct information on the local boundary-layer conditions at the rough walls. Measurements of shock speed and shock pressure ratio are presented for both smooth-wall and rough-wall flow over lengths of machined-smooth and rough strips which lined all four walls of the shock tube" (p. 1).