Report presenting an investigation in the transonic pressure tunnel to determine the afterbody pressure distribution and fin loading characteristics of two configurations of the TX-21 special weapon. The only different in the two configurations was the nose contour, with one having a hemispherical-flat shape and one with a double-radius ogive-flat shape. Results regarding the pressure port, fin loads, and force measurements are provided.

The work described in this report was done to determine the path of decomposition of plutonium (IV) oxalate and to determine the factors affecting the reactivity of the oxide with the hydrogen fluoride.

An experiment designed to evaluate the in-pile performance of the U-Mg fuel material when irradiated to high burnups has been completed. Twelve specimens of the fuel material which contained uranium particles that packed 50 volume per cent, (91.5 weight per cent), uranium in a magnesium matrix were canned in Zircaloy cans and irradiated in the Materials Testing Reactor to 0.1 (1000 MWD/T), 0.3 (5000 MWD/T), 1.0 (10000 MWD/T) and 2.0 20000 MWD/T) per cent burnup of the total uranium atoms; more exactly, 1 MWD/T = 1.16 x 10⁻⁴ per cent burnup of the total uranium atoms. Irradiation of the twelve capsules began on August 1, 1954. The burnup figures used in this report are calculated values assuming a conversion ratio for the capsules of 1.0. Because of the lack of confirmed experimental burnup data for exposures of this magnitude, there is a possible error in the calculated values of about 20 per cent at 2.0 per cent burnup. However, recent results based on chemical analysis for cesium indicate that the calculated values of burnup agree quite closely for the higher exposures. Burnup estimates based on the results of the chemical analysis will be published when they become available. Six of …

A report based on a study about the factors which affect the amount of chemical reaction between water and Zircaloy 2 at high temperatures. Also, experimental programs for the measurement of radiation emissivity, chemical reaction rates, and diffusion rates have been completed.

"Available experimental two-dimensional-cascade data for conventional compressor blade sections are correlated. The two-dimensional cascade and some of the principal aerodynamic factors involved in its operation are first briefly described. Then the data are analyzed by examining the variation of cascade performance at a reference incidence angle in the region of minimum loss" (p. 1).

Compendium presenting a comprehensive integration of available aerodynamic design information on axial-flow compressors. The subjects of the first volume of this investigation are objectives and scope, compressor design requirements, compressor design system, potential flow in two-dimensional cascades, and viscous flow in two-dimensional cascades.

Chapters XI to XIII concern the unsteady compressor operation arising when compressor blade elements stall. The fields of compressor stall and surge are reviewed in Chapters XI and XII, respectively. The part-speed operating problem in high-pressure-ratio multistage axial-flow compressors is analyzed in Chapter XIII. Chapter XIV summarizes design methods and theories that extend beyond the simplified two-dimensional approach used previously in the report. Chapter XV extends this three-dimensional treatment by summarizing the literature on secondary flows and boundary layer effects. Charts for determining the effects of errors in design parameters and experimental measurements on compressor performance are given in Chapters XVI. Chapter XVII reviews existing literature on compressor and turbine matching techniques.