From abstract: Detailed information is given on the theory, design, parts specifications and assembly data for a new radiation detector for measurement of ionizing radiations.

Report documenting the suitability of Iowa for plant locations to produce synthetic liquid fuels, based on raw materials. In this study, the only raw material considered in this survey was coal.

Report presenting an experimental investigation of the downwash and sidewash flow angles in a transverse plane behind a cruciform-wing and body combination. The wing-body combination had a cruciform arrangement of two identical triangular wings of aspect ratio 2.31 corresponding to a leading-edge sweep angle of 60 degrees placed on a body of fineness ratio of 16. The investigation was conducted at a specified Mach and Reynolds number and a range of angles of bank and attack.

Report presenting an investigation to determine the overall performance of a prototype model of the J47D (RX1-1) turbojet engine with a fixed-area exhaust nozzle. Data was obtained for a range of engine speeds, altitudes, and Mach numbers. Results regarding the effect of those variables and generalization in terms of pumping characteristics are provided.

From Summary: "This paper contains the results of measurements at 20 degrees and 60 degrees wing sweep of the low-speed pressure distribution on the wing, wing slat, wing leading-edge fillet, and fuselage of a 1/4-scale model of a preliminary Bell X-5 airplane design. The pressure-distribution measurements were made to obtain specific aerodynamic load information for application to the Bell X-5 airplane. Some of the results, however, are useful for application to swept-wing airplanes in general."

Report presenting the effect of control effectiveness of systematically varying the size and location of trailing-edge flaps on a 45 degree sweptback wing at a Mach number of 1.9. The wing model had an aspect ratio of 2.5, a taper ratio of 0.625, and 6-percent-thick hexagonal airfoil sections. Results regarding the rolling-moment and yawing-moment coefficients, lift, rolling-moment, and pitching-moment effectiveness parameters, and flap characteristics are provided.

From Summary: "The lift, drag, and pitching moment of a body of revolution are presented for Mach numbers from 0.60 to 0.92 and from 1.20 to 1.70. These data were obtained at test Reynolds numbers of 0.64 million, 1.02 million, and 1.59 million."

Report presenting an investigation in the free-flight tunnel to determine the dynamic lateral stability and control characteristics of a coupled airplane configuration with simplified fighter models attached to the wing tips of a simplified bomber model. The configuration is meant to represent fighter airplanes carried on the wing tips of a bomber airplane to provide fighter protection for the bomber or for in-flight fueling. Results regarding the fighters attached with freedom in roll, with freedom in roll and pitch, and with freedom in roll, pitch, and yaw are provided.

Report presenting measurements made at a Mach number of 0.25 of the aerodynamic characteristics of a wing with an aspect ratio of 3 combined separately with three geometrically similar bodies of revolution with the same fineness ratio but differing sizes. Results regarding wings, bodies of revolution, wing in the presence of the bodies, wing combined with the bodies of revolution, and effect of wing incidence changes are provided.

From Summary: "The linearized theory for compressible unsteady flow is used, as suggested in recent contributions to the subject, to obtain the velocity potential and the lift and moment for a thin harmonically oscillating, two-dimensional wing-aileron combination moving at sonic speed. The velocity potential is derived by considering the sonic case as the limit of the linearized supersonic theory. From the velocity potential explicit expressions for the lift and moment are developed for vertical translation and pitching of the wing and rotation of the aileron. The sonic results are compared and found to be consistent with previously obtained subsonic and supersonic results. Several figures are presented showing the variation of lift and moment with reduced frequency and Mach number and the influence of Mach number on some cases of bending-torsion flutter."

The results of an experimental investigation of the effect of oil inlet distribution and oil inlet temperature on the inner and outer-race temperatures of 75-millimeter-bore (size 215) cylindrical-roller inner-race-riding cage-type bearings are reported. A radial-load test rig was used over a range of dn values (product of the bearing bore in mm and the shaft speed in r.p.m) from 0.3 x 10(5) to 1.2 x 10(6) and static radial loads from 7 to 1113 pounds.

Introduction: "A corrosion test program, to determine the suitability of LaBour B-55 and Worthite for use in the construction of circulating pumps for th UO3 process has been completed and the data are appended."

Manual of operation for a neutron sensitive ionization chamber for reactor instrumentation.

Report presenting an investigation of an NACA 10-(1.7)(062)-057-27 two-blade swept propeller was conducted int he 16-foot high-speed tunnel over a range of blade-angle settings. Two related straight propellers were also tested over the same operating range as the swept propeller. Results regarding envelope efficiency, effect of compressibility on maximum efficiency, effect of sweep on power coefficient, constant-power propeller operation, and effect of sweep on propeller-blade loading are provided.