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Report presenting an investigation of the aerodynamic characteristics of various configurations of the Republic F-105 in the transonic tunnel at Mach numbers from 0.60 to 1.13. Results in this report include the static longitudinal stability and control characteristics, the effect of various configuration modifications on lift-drag ratio, the effect of subsonic and supersonic inlets and external stores, and the effect of area-distribution modifications on performance.

Memorandum presenting an application of the supersonic area rule concept to the deign of a straight-wing-body combination with large symmetrically mounted nacelles located at the 70-percent-semispan station. The pressure drag from the configuration with nacelles was found to be significantly less than that from a corresponding configuration without nacelles throughout the Mach number range.

A comparison of B and Hf for use in APPR control rods shows that it is possible to substitute Hf plate. Increased wall thickness of Hf will result in a smaller water volume, but reduction of the moderating center will not decrease the effectiveness of Hf rods. Burnup of Hf results in only small change of the initial blackness. Since neutron absorption in most of the Hf isotopes are (n, gamma ) reactions there is no heat generation in Hf rod. (W.L.H.)

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This paper discusses the estimated effects of silver salts from regeneration of iodine reactors on waste cribbing at Redox. (KJD)

Recent developments in the field of photoconductive devices made possible the simplification and attendant improvement of the recording anemometer system used with the portable meteorological mast. The purpose of the work was to produce a simple, reliable recording anemometer system compatible with the project's existing instrumentation. Of primary importance was reduction of maintenance without loss of accuracy. This report discusses some of the factors considered in the design of the system, describes in detail the electronic circuitry and mechanical components, and presents some performance data. The data obtained from a twenty-four hour trial run indicates that the system has fulfilled the requirements.

Results presenting an investigation in the supersonic pressure tunnel to determine the static stability and control characteristics of a ram-jet canard missile at Mach number 2.01. The missile had wings, canard surfaces of delta plan form with 70 degree swept leading edges, and two ram-jet nacelles. Results regarding the longitudinal and lateral characteristics are provided.

Report presenting an investigation of the aerodynamic characteristics of various configurations of a model of the Republic F-105 in the transonic tunnel at a variety of Mach numbers. Results regarding lift characteristics, pitching-moment characteristics, zero-lift drag characteristics, maximum lift-drag ratio, flaperon and rudder characteristics, and effective downwash characteristics are provided.

Report presenting a free-flight investigation of the control effectiveness of a differentially deflected horizontal tail. The results were compared with and found to be in general agreement with estimates derived from other free-flight tests, wind tunnel tests, and theory. Results regarding the rolling moment, yawing moment, and overall rolling effectiveness are provided.

Report presenting measurements of aerodynamic heat transfer at six stations on the 40-inch-long 10 degree total-angle conical nose of a rocket-propelled model at Mach numbers up to 5.9. Laminar, transitional, and turbulent heat-transfer coefficients were obtained for Mach numbers up to 4. Results regarding skin temperature time histories, boundary-layer transition, and calculated skin temperature are provided.

Report presenting an investigation in the high-speed 7- by 10-foot tunnel at a range of Mach numbers to determine the aerodynamic loads on finned and unfinned bodies in the presence of a swept wing. A tip-mounted body at 1.04 semispan and an underwing pylon-mounted body at 0.33 semispan were investigated. Results regarding the body loading characteristics and effect of angle of attack are provided.

Experimental values of damping in roll at zero angle of attack of the Bell X-1E research airplane and various combinations of components were obtained at 5 different Mach numbers. The damping in roll of the model was of the order predicted by theory. Results regarding the contributions of the airplane components and comparisons of experimental values with theoretical values are provided.