Describes methods for slaughtering, curing, and canning pork for later use.

A step-by-step guide to logging the forests of the northeastern United States. Includes information about the tools and equipment used, including axes, saws, and tractors, as well as the use of horses.

A topical, alphabetically arranged index to volumes 71-80 including experiment station records, publications reviewed, and foreign publications. In has a list of all editorial notes from the referenced volumes.

Describes the Agricultural Conservation Program and its role in safeguarding the food supply through soil conservation assistance.

Note presenting a low-turbulence wind tunnel investigation of an NACA 64A010 airfoil with a porous surface of sintered bronze to determine the reduction in section drag coefficient that might be obtained at large Reynolds numbers by use of suction to produce continuous inflow through the surface of the model. Results regarding the uncompartmented model, compartmented model, observations on stability of laminar boundary layer, and theoretical calculations are provided.

"A theoretical solution is obtained for the problem of the shear buckling of infinitely long simply supported elastic Metalite type sandwich plates. An approximate correction is suggested for the determination of the critical shear stresses of plates that buckle in the plastic range" (p. 1).

Report presenting an investigation of seven hot-pressed ceramics for possible gas-turbine application. The properties, short-time tensile strength, thermal-shock resistance, coefficient of liner expansion, and density were determined. The ceramics tested were magnesium oxide, titanium carbide, zirconium carbide, boron carbide, silicon carbide with boron carbide, zircon, and zirconia with lime.

Note presenting an approximate method developed to predict the location of detached shock waves ahead of two-dimensional and axially symmetric bodies. The method is based on the continuity relation, which is applied to the air that passes the sonic line.

Report presenting testing of five NACA airfoil sections intended for use in rotor blades in the two-dimensional low-turbulence tunnel. The airfoils varied in thickness and theoretical design lit coefficients. Results regarding pitching moment, lift, drag, and helicopter performance calculations are provided.

Note presenting experimental pressure-time measurements along with schileren photographs of the unsteady-flow phenomena initiated in constant-cross-sectional-area passages. The methods of calculation of the flow phenomena are based on the assumptions of one-dimensional, nonviscous, unsteady flow.

Note presenting thermodynamic properties of the products of combustion of five different mixtures of air with typical aircraft-engine fuel, which have been calculated from the most reliable thermodynamic data available. The calculations are presented in five charts of internal energy plotted against entropy with values of temperature, specific volume, pressure, and enthalpy indicated corresponding to five different percentages of the fuel-air ratio for perfect combustion.

Report presenting a comparison of the thermal performance and pressure-drop characteristics of heat exchangers on a heat-exchanger test stand. The exchangers included parallel and cross-flow units as well as extended-surface and all-prime-surface units.

Report presenting an investigation in free flight of the rolling effectiveness of plain ailerons in conjunction with wings having 0 and 45 degrees sweepback with several airfoil sections. Results regarding the rolling characteristics of rectangular and sweptback-wing configurations and drag measurements are provided.

Report presenting an evaluation of a piston-type gas-generator engine by comparing the performance of a transport airplane powered with than engine with the same airplane powered by different engines. The engines compared were a turbojet engine, a turbine-propeller engine, a compound engine, and a turbosupercharged reciprocating engine utilizing a variable-area exhaust jet nozzle. Results regarding optimum altitude and transport performance are provided.

Report presenting an investigation at a Reynolds number of 6,800,000 to determine the low-speed lateral control characteristics of a 20-percent-chord half-span outboard aileron on a wing with 42 degrees of sweepback at the leading edge. The lateral control, aileron hinge-moment, aileron load, and balance-chamber-pressure characteristics were determined for the wing with and without high-lift and stall-control devices for an angle-of-attack range from -4 degrees through the stall.

Report presenting an investigation in the two-dimensional low-turbulence tunnel of a symmetrical airfoil section equipped with a 0.30-airfoil-chord sealed internally balanced flap with a 0.70-flap-chord overhang and a 0.33-flap-chord leading tab. Results regarding airfoil lift, surface pressure, flap hinge-moment, and flap-balance-chamber pressure characteristics at various flap deflections.

Memorandum presenting aerodynamic characteristics of the NACA 64-010 and 64A010 airfoil sections as determined from wind-tunnel tests at Mach numbers from 0.3 to 0.9. Comparisons are made which indicate the only significant differences in the characteristics of the two sections to be a consistently greater lift-curve slope and an approximately 10-percent greater maximum section lift coefficient at Mach numbers above 0.7 for the NACA 64-010 airfoil section.

Report presenting the effect of flutter characteristics of variation on the aerodynamic shape of concentrated weights rigidly mounted on a simplified wing structure. Two general types of weights with similar mass and moment-of-inertia properties were employed. Results regarding effects of aerodynamic shape of concentrated weights, effects of spanwise variation of light concentrated weights, and effects of moment of inertia of light concentrated weights.

Report presenting testing in the X-4 airplane to obtain stability and control data. The flight was made with the center of gravity at 19.7 percent of the mean aerodynamic chord and with the rudder-boost system removed. The results showed that the longitudinal stability was positive in the clean condition and in the gear-down flaps-up condition.

From Summary: "Results of wind-tunnel tests are presented for a wing with the leading edge swept back 63^o and of symmetrical section in combination with a body at Mach numbers from 0.5 to 0.95 and from 1.09 to 1.51."

Memorandum presenting an investigation of a typical inlet stage of a multistage axial-flow compressor that was designed on the basis of an analysis of basic design variables. The stage, consisting of 19 rotor blades and 20 stator blades with 40 inlet guide vanes, had a hub-to-tip-radius ratio at the rotor inlet of 0.50 and a rotor-blade outside diameter of 14 inches. Results regarding the overall compressor performance, comparison of compressor performance with design, and rotor-row performance are provided.

From Introduction: "This paper presents the results of the investigation of the wing-alone and wing-fuselage configurations employing a wing with the quarter-chord line swept back 45^o, aspect ratio 4, taper ratio 0.3, and an NACA 65A006 airfoil section parallel to the stream."

From Summary: "A determination of the dynamic characteristics of a typical turbojet engine with a centrifugal compressor, a sonic-flow turbine-nozzle diaphragm, and fixed area exhaust nozzle is presented. A generalized equation for transient behavior of the engine was developed; this equation was then verified by calculations using compressor and turbine performance charts extrapolated from equilibrium operating data and by experimental data obtained from an engine operated under transients in fuel flow."

The characteristics of a cargo-dropping device having extensible rotating blades as load-carrying surfaces have been studied in simulated vertical descent in the Langley 20-foot free-spinning tunnel. The investigation included tests to determine the variation in vertical sinking speed with load. A study of the blade characteristics and of the test results indicated a method of dynamically balancing the blades to permit proper functioning of the device.