Memorandum presenting the carpet-plotting technique as a more useful and concise method of summarizing the 65-series compressor-blade cascade data. Four different carpet plots are presented. A sample use of the carpet plots is also provided.

Report presenting an investigation in the supersonic wind tunnel to determine the thrust and pumping characteristics of a series of ejector exhaust nozzles. Results indicated that the free-stream Mach number had no effect on those characteristics of the ejectors in the range for which the secondary flow was choked.

Report presenting chordwise pressure distributions measured over the left wing of the Convair XF-92A delta-wing airplane to determine the effect of lift on the wing characteristics at subsonic and transonic Mach numbers. Results regarding the chordwise pressure distributions, wing-section aerodynamic characteristics, spanwise distribution, and elevon-section loads are provided.

Report discussing the low-speed stability and control characteristics of a modified model of the MX-1554A with a triangular wing and triangular stabilizing surfaces, which are designed to give more satisfactory stability and control than previous versions. Other modifications included an increase in slotted-flap span, redesigned tip aileron, fuselage tail cone, and speed brakes. Results provided include the effect of flow-control devices, tank and pylon location, a ground board, rotary stability derivatives, and a single support strut on the stability, control, and aerodynamic characteristics.

Report presenting an investigation in the Langley Unitary Plan wind tunnel to determine the drag and static longitudinal and lateral stability characteristics of a model of the Grumman F11F-1F airplane at Mach numbers 1.56, 1.76, 2.06, and 2.53. The investigation included the effects on performance and stability of modifications, including a wing-root leading-edge fillet and horizontal tails with negative dihedral of 10 degrees and 30 degrees. Information regarding net external minimum drag coefficients, neutral points, directional stability, and positive effective dihedral is provided.

Report presenting an investigation of the low-speed stability and control characteristics of a 1/15-scale free-flying model of the Convair XB-58 airplane. Results regarding the longitudinal stability and control and a pod-drop investigation are provided.

Report presenting the overall performance and rotating stall characteristics of a single-stage compressor with a hub-tip ratio of 0.76 and a symmetrical velocity diagram over a wide range of weight flow for several different design speed percentages. No discontinuities in performance were noted at an operating condition. Results regarding the overall performance, types of rotating stall observed, circumferential extent of stall zones, flow fluctuations incited by rotating stall, rotating-stall hysteresis, and a theoretical analysis are provided.

A study of mixtures of pure methanol and trimethyl borate showed that the composition can be accurately obtained by a simple density determination. The refractive-index determination gives the composition with much less accuracy. The potentiometric titration of boric acid is also discussed.

Report presenting a technique and the results obtained of wind-tunnel forced-oscillation tests on a model of the Douglas D-558-II airplane which was instrumented to obtain the dynamic cross derivative and static derivative. Tests were conducted for a range of Mach numbers and angles of attack. Results regarding sample calculations of the period and damping of the full-scale airplane are provided despite not being conclusive due to the inadequate number of flight conditions investigated.

"A transonic turbine with a stator trailing-edge thickness reduced from 0.030 to 0.010 inch has been investigated experimentally. The performance results indicated an increase in efficiency of 0.6 of a point at design operation, and as much as 2.4 points at off-design conditions, as a result of reducing the trailing-edge thickness. This improvement could only be partially accounted for by the theoretical change in mixing loss for the two stator-blade rows, and it was felt that the improvement was largely due to a reduced amount of low-velocity fluids entering the rotor and the interference effect of these fluids with the mainstream flow" (p. 1).

Report presenting an investigation of the ditching characteristics of the Boeing 707 jet transport in tank no. 2. Various conditions of damage, landing attitude, and speed were investigated. Data were obtained from visual observations, acceleration records, and motion pictures.

"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 the effect of free-stream Reynolds number, engine installation, and model scale on inlet stability limits and on the amplitude and frequency of buzz. The data were taken at a free-stream Mach number of 2.0 and angles of attack from 0 to 6 degrees. Results regarding free-stream Reynolds number effect, model scale, and effect of engine on stability are provided.

Report presenting testing of the Republic F-105 at low speeds to determine the results of additional longitudinal stability tests of measurements of the hinge moments and normal force of the all-movable horizontal tail on a model equipped with a supersonic-type elliptical wing-root inlet.

Report discussing an experimental investigation to determine the aerodynamic characteristics of the Army Chemical Corps model E112 bomblets. From Summary: "A detailed analysis has not been made; however, the results showed that a gap between model tips and the end plates or increasing the end-plate size for a solid model could result in a spirally stable configuration." A large amount of data collected from testing and photographs of the model are provided.

Report presenting a compilation of sea-level static and flight-performance data for existing and designed U.S. axial-flow turbojet and ram-jet engines. Factors considered include engine size, performance, and weight, and actual and theoretical performances are compared.

Report discussing tests performed with a rocket-boosted model of the McDonnell F4H-1 airplane at transonic and supersonic speeds. Special attention is given to the external drag coefficient at various Mach numbers. Large pitching oscillations were also noted at Mach numbers between 0.20 and 1.17, which made it impossible to determine the drag at that range.

Memorandum presenting an airborne missile simulator used to represent visually the predicted flight behavior of the Navy XASM-N-7 Bullpup air-to-surface missile, which is guided along the line of sight to the target by bang-bang radio signals controlled by the pilot of the launch airplane. Quantitative response measurements showed that the simulator gave a good representation of the trajectory and control characteristics predicted for the Bullpup missile, and the simulation appeared plausible to the pilots.

From Summary: "The reactor operating conditions were varied to enable selection of values giving a good compromise between low uranium investment and loss gross weight at each altitude and flight Mach number considered. The corresponding values of reactor and missile operating conditions are presented in the report."

Memorandum presenting an investigation of an airplane model to determine the effect of area suction trailing-edge flaps and several leading-edge modifications on the aerodynamic characteristics of a 45 degree sweptback wing. The wing had an aspect ratio of 2.8 and a taper ratio of 0.17.

Report discussing an investigation to determine the cause and provide a fix for the instability in flight of the antisubmarine rocket Mk 1 Mod 0. The Magnus effects and their nonlinear variation with angle of attack were found to affect the stability, so reducing the Magnus effects should reduce instability in the missiles. The greatest reduction of Magnus effects was found through a combination of nose-ring spoiler and the original direction of the propeller rotation, but the nose ring increased the drag.

Report discussing an investigation into the performance of several modifications of a side-inlet ramjet engine diffuser. Total-pressure-recovery profiles, Mach number profiles, longitudinal wall static pressure distributions, and variation of the average-static to average-total pressure are presented.

Report presenting low-speed testing of the Republic F-105 airplane in the pressure tunnel to determine the plane's lateral control and directional stability and control characteristics. Various combinations of components were tested, including tares, spoilers, ailerons, and wing fences.

"A porous wall was used in an attempt to eliminate reflections of oblique waves from a tunnel wall. Calculations were made of the required resistance characteristics of a wall in order that the flow through the wall, due to the pressure difference across a shock wave, would equal the component normal to the wall of the flow behind the shock wave. The resistance characteristic of a sintered bronze wall was measured and the reflections of waves impinging on the wall were observed at a Mach number of 1.62" (p. 1).