Buffet boundaries, buffeting-load increments for the stabilizers and elevators, and buffeting bending-moment increments for the stabilizers and wings as measured in gradual maneuvers for a jet-powered bomber airplane are presented. The buffeting-load increments were determined from strain-gage measurements at the roots or hinge supports of the various surfaces considered. The Mach numbers of the tests ranged from 0.19 to 0.78 at altitudes close to 30,000 feet. The predominant buffet frequencies were close to the natural frequencies of the structural components. The buffeting-load data, when extrapolated to low-altitude conditions, indicated loads on the elevators and stabilizers near the design limit loads. When the airplane was held in buffeting, the load increments were larger than when recovery was made immediately.

From Summary: "Experimental force, moment, and center-of-pressure variations for a large number of bodies of revolution have been compared with the calculated characteristics based on the approximate theory developed in NACA-RM-A9I26. The bodies varied in fineness ratio from 4.5 to 21.1, from blunt unboattailed bodies to airship hulls, and the experimental results are given for widely varying Mach number ranges of angle of attack. It is shown that the lift and drag characteristics are fairly accurately predicted by the theory but that the actual center of pressure is more rearward than the theory indicates."

Report presenting charts to provide a convenient means for obtaining the derivatives of rotor resultant force, rotor pitching amount about the helicopter center of gravity, and rotor torque with respect to rotor angle of attack, forward speed, rotor speed, and collective pitch.

Report issued by the Argonne National Laboratory discussing a progress report on the Argonne-Oak Ridge digital computer. This report is an interim report, whose primary value is that it has forced those engaged in the work to give concrete expression to what they have been doing and thinking about up to this point. This report includes tables, illustrations, and photographs.

Report presenting an experimental investigation to determine the combustion properties of aluminum as a fuel for use in high-speed aircraft. The aluminum fuel was injected both in powder and wire form into 2-inch-diameter ramjet-type combustors. Results regarding operational problems, thrust, and combustion efficiency are provided.

A preliminary reserve statement regarding Reserve Blocks B and C, as well as Mineral Channels 10 and 12 of the Outlaw Mesa, located in Mesa County, Colorado.

From Summary: "A low-turbulence wind-tunnel investigation was made of an NACA 64A010 airfoil having a porous surface to determine the reduction in section total-drag coefficient that might be obtained at large Reynolds numbers by the use of suction to produce continuous inflow through the surface of the airfoil (area suction). In addition to the experimental investigation, a related theoretical analysis was made to provide a basis of comparison for the test results."

Report presenting a description and results of an investigation of a model of the XH-17 two-blade, jet-powered helicopter. Tests were made with a standard configuration and with several modifications, including varying the size of blade counterweights, changing the control stiffness and chordwise bending stiffness of the blades, and varying the pylon and undercarriage damping and spring constants. Results regarding flutter testing, ground-vibration tests, and three-per-revolution rotor-blade unsymmetric bending oscillations are provided.

This report discusses the production of large-diameter zirconium crystal bars in a 16 inch diameter, Hastelloy B, de Boer unit in order to increase production efficiency.

Report presenting an analysis of a series of wing-body combinations in the 8-foot high-speed tunnel. The paper presents the results of an investigation of a wing-fuselage combination with a wing of unswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and an NACA 65A006 airfoil section. Results regarding force and moment characteristics and wake and downwash characteristics are provided.

Report presents the results of a flight investigation conducted on a typical high-wing personal-owner airplane to determine the effect of control centering springs on apparent spiral stability. Apparent spiral stability is the term used to describe the spiraling tendencies of an airplane in uncontrolled flight as affected both by the true spiral stability of the perfectly trimmed airplane and by out-of-trim control settings. Centering springs were used in both the aileron and rudder control systems to provide both a positive centering action and a means of trimming the airplane.

Report presenting local coefficients of convective heat transfer as measured from skin temperature along the body of an RM-10 NACA research missile, which consisted of a parabolic body of revolution. Results regarding recovery factors, adiabatic wall temperatures, Nusselts, Prandtl, and Reynolds numbers, and boundary-layer transition are provided.

"A wind-tunnel investigation of a 0.049-scale model of the Boeing XB-52 airplane was made at Mach numbers from 0.30 to 0.925 and at corresponding Reynolds numbers from about 2.3 x 10(exp 6) to 4.3 x 10(exp 6). The results of the investigation indicate satisfactory static longitudinal stability throughout the test Mach-number range and some loss in tail effectiveness beginning at about 0.80 Mach number. A comparison of the results of these tests with those of the same model in the Boeing Airplane Company's wind tunnel showed close agreement of lift- and drag-divergence Mach numbers. Slight differences were observed in tail effectiveness and the position of the stick-fixed neutral point."

Report describing an investigation conducted with a single combustor from a J47 turbojet engine using weathered aviation gasoline and several spark-plug modifications to determine altitude ignition, acceleration, and steady-state operating characteristics. Results regarding ignition, acceleration, altitude operational limits, combustion efficiency, and pressure loss are provided.

Report presenting time histories of the aerodynamic loads on the vertical and horizontal tail surfaces of a jet-powered bomber airplane (B-45A) in sideslip maneuvers. Information about maximum measured rudder and fin loads, maximum total vertical-tail load, horizontal-tail-load dissymmetry, maximum elevator loads, and elevator-load dissymmetry is provided.

Report presenting a pressure-distribution investigation of a body of revolution in the 4- by 4-foot supersonic tunnel at a Mach number of 1.59. Results regarding the basic pressure-distribution data, reduction of conical-pitot-yaw-head data, four-static orifice system, flow-angle determination, other orifice systems, and general comments on theoretical prediction of pressure distribution on cone surfaces are provided.

Report presenting the drag-reducing effectiveness of bleeding air to the base region of blunt-base bodies in a supersonic stream was investigated at a Mach number of 1.91.

From Summary: "As part of a study of means of airspeed measurement at transonic speeds the use of static orifices located ahead of the wing tip has been investigated for possible application to service or research airspeed installations. The local static pressure and local Mach number have been measured at a distance of 1 tip chord ahead of the wing tip of a model of a swept-wing fighter airplane at true Mach numbers between 0.7 and 1.08 by the NACA wing-flow method. All measurements were made at or near zero lift. The local Mach number was found to be essentially equal to the true Mach numbers less than about 0.90."

A complete investigation was made of the r-f field in the 1/10-scale Materials Testing Accelerator (Mark I) cavity

Memorandum presenting a wind-tunnel investigation of the low-speed, static, lateral and directional characteristics of a model of an early design of the X-3 airplane with the wing flaps neutral and deflected. The model utilized a wing with an aspect ratio of 3.01, a 4.5-percent-thick hexagonal section, and a taper ratio of 0.4. Results regarding lateral stability and control with the flaps neutral, with the flaps fully deflected, with miscellaneous additions to the complete model, directional stability and control with the flaps neutral, with the flap fully deflected, with miscellaneous additions to the complete model, and oscillating rolling moments are provided.

Report issued by the U.S. Bureau of Mines investigating the well patterns and spacing of the Paola shoestring reservoir in Kansas. Several methods of field tests are presented. The report includes illustrations and tables.

"An investigation was conducted at the NACA Lewis laboratory to determine whether simulated porous gas-turbine blades fabricated by the Eaton Manufacturing Company of Cleveland, Ohio would be satisfactory with respect to coolant flow for application in gas-turbine engines. These blades simulated porous turbine blades by forcing the cooling air onto the blade surface through a large number of chordwise openings or slits between laminations of sheet metal or wire. This type of surface has a finite number of openings, whereas a porous surface has an almost infinite number of smaller openings for the coolant flow" (p. 1).

Memorandum presenting a determination of the thermal conductivity of 14 metals and alloys in temperatures ranges with a maximum of 1100 degrees Fahrenheit. Some of the metals included steels, high-temperature alloys, molybdenum disilicide, aluminum alloys, brass, and silver. A comparison method was used to obtain the results in which the thermal conductivity of the test sample was compared with the conductivity of high-purity lead.

Report presenting testing of a 6.5-inch-diameter ramjet engine with a design Mach number of 2.13 and a short-flame-length combustor. Performance characteristics are provided for a range of Mach numbers and fuel-air ratios. Results regarding thrust, drag tests, static pressure, and combustion efficiencies are provided.