Provides recipes using evaporated apple rings as the main ingredient. (Evaporated apples contain more moisture than traditional dried apples.)

Describes how to recognize rust-spreading barberry bushes and how to kill them. Explains how doing so can be beneficial both to individual farmers and the national economy.

From Summary: "Procedures for applying these analytical methods to experimentally measured blade-metal temperatures are presented. Data are presented for the leading and trailing edge of a symmetrical water-cooled blade to illustrate the validity of the methods for those portions of the blade. In addition to the application to turbine blades, the methods can be applied to any heat-transfer apparatus having a profile that can be approximated by the shape discussed."

"Model investigations were made to determine the ditching characteristics of three typical multiengine airplanes equipped with possible arrangements of hydro-ski ditching gear. The behavior of the models was determined from visual observations, acceleration records, and motion pictures of the landings. Data are presented in tabular form and sequence photographs" (p. 1).

Report presenting an untapered aluminum-alloy box beam representing the main structural component of a full-span, two-spar, 45 degree swept wing with a carry-through section subjected to antisymmetrical tip bending and twisting loads such that stresses were kept below the proportional limit. Results regarding stresses due to antisymmetrical bending, stresses due to antisymmetrical torsion, distortions due to antisymmetrical bending, and distortions due to antisymmetrical torsion are provided.

"Simple, sufficient conditions are given under which a two-dimensional steady compressible flow can be continued across the line of Mach number 1 as a continuous supersonic flow. Methods for the actual computation of the flow are described. The problem is of importance in the theory of transonic flows past airfoils" (p. 1).

Note presenting a method by which the energy and continuity relations are simultaneously solved to express the velocity distributions downstream of any compressor blade row in terms of outlet total temperature, total pressure, and relative flow angle. The method is intended for use in units in which only a limited amount of experimental data can be obtained.

Report presenting sound-pressure measurements at static conditions for five shrouded propellers and a comparison with those for an unshrouded propeller of the same diameter operating at approximately the same rotational speed and power. Results regarding total sound, frequency analysis, shroud chord, tip clearance, tip speed, and number of blades are provided.

Note presenting results of tests on duplicate longitudinal and transverse specimens of aluminum-alloy 75S-T6 sheets with nominal thicknesses of 0.032, 0.064, and 0.125 inch. Results are presented in the following forms: tensile and compressive stress-strain graphs and stress-deviation graphs, graphs of tangent modulus against stress in compression, auxiliary graphs for estimating plastic buckling stress, stress-strain graphs for tensile specimens tested to failure, and graphs of local elongation and of elongation against gage length for tensile specimens tested to fracture.

Report presenting force and moment data obtained at low speeds to determine the aerodynamic characteristics of an unswept untapered semispan wing of NACA 64A010 section and aspect ratio 3.13 equipped with 25-percent-chord unsealed plain flaps with various spans and spanwise locations. Lift, drag, pitching-moment, and flap hinge-moment data were obtained for the wing with the flaps deflected up to 60 degrees.

Note presenting an investigation to determine some of the strength and elastic properties of honeycomb-type core materials fabricated from resin-impregnated rayon-mat fabrics. Eight blocks of core material were made using the corrugation method and the cores were made of rayon fabrics corrugated either parallel or perpendicular to the preferred direction of the individual fibers of the mat. The results indicated that the core materials do not appear to be better overall materials for use in sandwich construction than resin-impregnated paper honeycomb cores of equal density.

The theory of elasticity shows that the maximum stress at a circular hole in an infinite plate in tension is three times the applied stress when the material remains elastic. The effect of plasticity of the material is to lower this ratio. This paper considers the theoretical problem of the stress distribution in an infinitely large sheet with a circular hole for the general case where the material may have any stress-strain curve. The plate is assumed to be under uniform tension at a large distance from the hole. The material is taken to be isotropic and incompressible. (author).

Report presenting an investigation of the two-dimensional aerodynamic characteristics of three airfoil sections formed by removing various portions of the original chord from the trailing edge of the NACA 0012 airfoil section. Results regarding lift, drag, and pitching moment and aerodynamic center are provided.

Note presenting an investigation in the free-flight tunnel to determine the dynamic longitudinal stability as influenced by the static stability measured in wind-tunnel force tests under conditions of constant thrust and constant power. The results indicated that reductions in constant-thrust static stability caused a decrease in the longitudinal steadiness.

Report presenting an investigation to determine the effect on friction of films formed on steel surfaces by decomposition of common lubricants of several types. The films were formed by heating, in air, surfaces to which a thin film of fluid lubricant had been applied. Results regarding the fluid lubricants, decomposition films, surface loading, fluid lubricant on decomposition film, and practical significance are provided.

Report presenting a smooth-water-landing investigation with a small seaplane to obtain experimental wing-bending-moment time histories together with time histories of the various parameters necessary for the prediction of wing bending moments during hydrodynamic impact. Experimental results were compared with calculated results, including inertia-load effects and the effects of air-load variation during impact.

Report presenting the effect of aspect ratio on the air forces and moments of an oscillating flat rectangular wing in supersonic potential flow.

Report presenting a method for determining the horizontal tail loads in maneuvering flight. The method is based on the assignment of a load-factor variation with time and the determination of a minimum time to reach peak load factor. Consideration is given to the maximum tail loads, maximum pitching accelerations, and maximum pitching velocities obtainable.

Note presenting a transformation theory of systems of partial differential equations which allows the construction of classes of pressure-density relations depending on parameters for which the equations governing the flow can be transformed into an essentially simpler form, into the system corresponding to the wave equation in the subsonic region, and finally into the form corresponding to the Tricomi equation in the transonic region.

Report presenting a method of relating the effects of fuel-air ratio on the knock-limited charge flow and power of a supercharged engine with those of compression ratio and inlet-air temperature. Knock data obtained in a CFR engine over a wide range of conditions were correlated with eight fuels: 28-R fuel, aviation alkylate, S reference fuel, diisopropyl, triptane, cyclohexane, cyclopentane, and triptene.

Report presenting an analysis of the effect at design condition of inlet hub-tip-radius ratio and mass flow per unit frontal area on the allowable rotor-tip speed, pressure ratio, and power input per unit frontal area of multistage axial-flow compressors with approximately symmetrical velocity diagrams at all radii, constant total enthalpy along the radius, a maximum Mach number of 0.8 for all stages, and a prescribed empirical turning limitation. The analysis indicated that for any given hub-tip-radius ratio, the design rotor speed and pressure ratio per stage decrease with increasing design mass flow per unit frontal area.

Report presenting an investigation of the cooling characteristics of a multicylinder liquid-cooled engine of 1650-cubic-inch displacement. The results showing the variation of the cylinder-head temperature and the coolant heat rejection with the pertinent engine and coolant variables are provided. Data included a variety of engine power outputs, engine speeds, manifold pressure, fuel-air ratio, inlet-air temperature, ignition timing, exhaust pressure, coolant flow, composition, temperature, and pressure.

"Knock ratings are given for 23 ethers, each blended with base fuels. A.S.T.M. Aviation, A.S.T.M. Supercharge, aircraft single-cylinder, and 17.6 engine ratings are presented. Fuel consumption, blending characteristics, temperature sensitivity, and lead susceptibility are also briefly discussed" (p. 1).

Report presenting charts that permit the determination of enthalpy change for various processes regarding the thermodynamic data of gas properties. Some examples using the charts to solve problems are provided.