Note presenting tests of a hydraulic-power-controlled helicopter to determine the effect of friction in the servovalves and the effect of stick friction when the valve friction is present. The tests showed that, when the valve friction is equivalent to about 1 3/4 pounds of force at the stick, precision flying is difficult and more work is required of the pilot.

From Summary: "A statistical study is made of icing data reported from weather reconnaissance aircraft flown by Air Weather Service (USAF). The weather missions studied were flown at fixed flight levels of 500 millibars (18,000 ft) and 700 millibars (10,000 ft) over wide areas of the Pacific, Atlantic, and Arctic Oceans. This report is presented as part of a program conducted by the NACA to obtain extensive icing statistics relevant to aircraft design and operation. The thousands of in-flight observations recorded over a 2- to 4-year period provide reliable statistics on icing encounters for the specific areas, altitudes, and seasons included in the data."

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From Summary: "This paper briefly summaries the more important statistical data obtained by the NACA on the subject of ground loads. The information presented relates primarily to landing-impact and taxiing loads; however, some limited data are also presented on one phase of ground-handling loads, namely, braking friction. A number of experimental and theoretical papers dealing with various aspects of the subject are listed in the bibliography."

Monthly magazine discussing natural resources, parks, hunting and fishing, and other information related to the outdoors in Texas.

Monthly journal about library issues in Texas including collection development, programming and activities, managements, and other topics of interest.

Sinusoidally oscillating downwash and lift produced on a simple rigid airfoil were measured and compared with calculated values. Statistically stationary random downwash and the corresponding lift on a simple rigid airfoil were also measured and the transfer functions between their power spectra determined. The random experimental values are compared with theoretically approximated values. Limitations of the experimental technique and the need for more extensive experimental data are discussed.

Note presenting equations of motion derived for the dynamic response of an aircraft to random atmospheric gust loads. The equations include the degrees of freedom of plunging, pitching, rolling, and an arbitrary number of elastic normal modes. Results for simplified cases show that unsteady aerodynamic theory is not important for increasingly large values of the turbulence scale compared with values of the wing chord.

Report presenting a theoretical investigation to study the effects of systematic changes in configuration of a representative airframe on the center-of-pressure travel due to changes in angle of attack and Mach number. The airframe was an unbanked canard missile configuration with low-aspect-ratio coplanar wing and tail surfaces of triangular plan form.

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Note presenting an analysis which predicts the skin-friction and heat-transfer characteristics of a compressible, laminar boundary layer on a solid flat plate preceded by a porous section that is transpiration cooled. The analysis is restricted to a Prandtl number of unity and linear variation of viscosity with temperature. Results regarding a comparison of polynomial and exact velocity distribution, skin friction, heat transfer, and some practical implications of results are provided.

Report presenting a derivation of the lateral motions of an airplane flying through continuous random isotropic turbulence in terms of three different functions and sets of forces. Three airplanes of different size are used to demonstrate the method, illustrate characteristic trends, and exhibit some simplifications possible in the calculations.

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A method is presented for the approximate solution of the nonlinear equations transonic flow theory. Solutions are found for two-dimensional flows at a Mach number of 1 and for purely subsonic and purely supersonic flows. Results are obtained in closed analytic form for a large and significant class of nonlifting airfoils. At a Mach number of 1 general expressions are given for the pressure distribution on an airfoil of specified geometry and for the shape of an airfoil having a prescribed pressure distribution. Extensive comparisons are made with available data, particularly for a Mach number of 1, and with existing solutions.

"The subject of beam loading in linear electron accelerators has been discussed. With suitable design it is possible to place the equilibrium electron phase angle well ahead of the crest of the traveling wave in the accelerator. With beam loading the equilibrium position will move toward the crest, but the electron energy will remain constant or nearly so over a considerable range of loading. Some loss in energy will result from moving the equilibrium phase angle off the wave crest but the spread in energies due to beam loading should be reduced.

This technical report described the formulation of a set of two-group neutron diffusion equations and the solution for the critical fuel cross section in a one-dimensional, multi-region spherical reactor. A subsequent report will describe the ORACLE code developed for survey calculations using this method.

From Abstract: "This report presents the results of field reconnaissance and office study of available data pertaining to the Cedar Mountains area, Emery County, Utah, and is part of a series of reports synthesizing the geologic relations of uranium deposits in all formations on the Colorado Plateau."

This report presents field reconnaissance results and office study of available data pertaining to the Cedar Mountain area, Emery County, Utah, and is part of a series of reports synthesizing the geologic relations of uranium deposits in all formations on the Colorado Plateau.

A description is given of the valve operating system for the PWR. The valves served by this system are a component pant of the following systems: reactor coolant system; pressurizer and pressure relief system; coolant discharge and vent system; and failed element detection and location system. (W.L.H.)

From Summary: "A variational theorem is presented for a body undergoing creep. Solutions to problems of creep bending and creep collapse of plates, columns, beams, and shells can be obtained by means of the direct methods of the calculus of variations in conjunction with the stated theorem. The application of the theorem is illustrated for plates and columns by the solution of two sample problems."

"The theory of cascades, made up of a series of flat plates placed one behind the other, is extended to the case where the impinging stream is not uniform, and the deduced properties of this cascade-flow are then applied to the study of the wall interference between such as cascade-like boundary and a vortex-source type of singularity. It is shown that the induced velocities, produced by the presence of such a wall, are equal to what is obtained by action of a suitably chosen 'reflected' singularity situated on one side of the wall, together with the action of another suitably chosen 'transmitted' singularity placed on the other side" (p. 1).