Report presenting an investigation of an 18-foot-radius helicopter rotor powered by tip-mounted ramjet engines in the helicopter test tower. The engine performance is compared with the performance determined in a previous investigation of a 9-foot-radius rotor with the same engines at similar speeds but with twice the centrifugal forces. Results regarding the propulsive characteristics, minimum specific fuel consumption and corresponding propulsive thrust, and operational characteristics are provided.

Report presenting a free-flight investigation of a rocket-powered research model to determine the hinge-moment and normal-force characteristics of a trailing-edge control on a delta wing between Mach numbers of 0.50 and 1.26. The hinge-line location of 40 percent control chord satisfactorily reduced the high hinge moments associated with plain flap-type controls. Results regarding hinge moments and normal force are provided.

This report describes progress in testing nonaqueous extractive methods for leaching Western ores of uranium and vanadium

This is a photogeologic map, scale 1:24,000, of MOAB-13 in Emery and Grand Counties, Utah.

This is a photogeologic map, scale 1:24,000, of Carlisle-2, San Juan County, Utah.

From abstract: "The inert-gas metal-arc welding process was used to determine weldability studies of various aluminum alloys that are being considered for use as can materials. The solid-phase and induction welding processes were also investigated for making can closures."

Abstract: "A possible method of cooling a liquid-fuel reactor is by spraying liquid metal through the liquid fuel, and then circulating the liquid metal through a heat exchanger. To evaluate the effectiveness of this cooling method, a few simple experiments were made with mercury sprayed through water. On the basis of the results, it was concluded that this method was intrinsically a low-power-density method, which could not find application except where a low fissionable-material inventory was the dominating requirement in a low-power reactor. Even there, it is thought that a boiling homogeneous reactor might be superior. The results are reported, in spite of their probably lack of value in the reactor program, simply to make the record complete."

Abstract: "The height changes produced by vertical electronic diffusion in the presence of negative ions are examined in some detail. Application of the results to the E-layer shows that a previous qualitative discussion remains valid."

"Theoretically derived charts and equations are presented by which tail-rotor design studies of directional trim and control response at low forward speed can be conveniently made. The charts can also be used to obtain the main-rotor stability derivatives of thrust with respect to collective pitch and angle of attack at low forward speeds. The use of the charts and equations for tail-rotor design studies is illustrated. Comparisons between theoretical and experimental results are presented. The charts indicate, and flight tests confirm, that the region of vortex roughness which is familiar for the main rotor is also encountered by the tail rotor and that prolonged operation at the corresponding flight conditions would be difficult" (p. 1).

Report discussing testing on a model of the proposed MX-1554A design to determine its stability and control characteristics in high speed flight. Information about the effect of speed brakes, tanks, and fences on the longitudinal characteristics is also provided.

Report issued by the Bureau of Mines over studies conducted on the dust exposure to mine workers. Contents of dust produced from drilling are noted. Health hazards of drilling dust is also presented. This report includes tables, and graphs.

Report presenting a perturbation method for the calculation of velocity and temperature profiles and skin-friction and heat-transfer characteristics for two-dimensional, compressible laminar boundary layers with heat transfer and a small arbitrary pressure gradient is presented. The combined effects of heat transfer and pressure gradient on boundary-layer characteristics are demonstrated by applying the results of the analysis to two representative wings.

Report presenting an investigation of the hazard of igniting airplane crash fires by electrostatic sparks, which are generated when detached airplane parts fly through clouds of dust and fuel mist. Within the limits of variables studied, the rates with which airplane wreckage collected a charge were directly proportional to the rate at which clay dust or fuel mist was intercepted. Results regarding the experimental charging of airplane parts, electrostatic ignition hazard, and investigation of protective coating are provided.

"Equations were developed for the torsional motion of a gas-turbine engine geared to a helicopter rotor in which the rotor blades were hinged to the rotor shaft. The rotor system was simplified to yield simple third-order equations that can be used in the analysis of engine control. Comparison of the system response calculated from these equations with the experimentally observed frequency response of a rotor from a 2500-pound helicopter showed satisfactory agreement" (p. 1).

Report presenting an investigation in several NACA wind tunnels to determine transition Reynolds numbers on a 10 degree cone at zero angle of attack. The trends of transition Reynolds number with stream Reynolds number and Mach number are not consistent across the different tunnels. These inconsistencies are attributed to variations in free-stream turbulence, flow irregularities introduced by compressor systems, and other airstream disturbances like compression- or expansion-wave boundary-layer interactions.

Report presenting secondary flow tests on an accelerating elbow with 90 degrees of turning designed for prescribed velocities that eliminate boundary-layer separation by avoiding local decelerations along the walls. Secondary flows were investigated for six boundary-layer thicknesses generated on the plane walls of the elbow by upstream spoilers. Results regarding the downstream total-pressure distribution and spanwise wall-static-pressure distributions are provided.

From Summary: "Axial-load fatigue tests at a stress ratio of zero were performed on notched and unnotched sheet specimens of 61S-T6 aluminum alloy and 347 and 403 stainless steels. Special emphasis was placed on tests at high stress levels which produce failures in small numbers of cycles."

Report presenting measurements of velocity profiles and skin friction in subsonic turbulent boundary layers with adverse pressure gradients. The skin friction in an adverse pressure gradient was found to decrease steadily with distance to a value approaching zero for the region of separation. Results regarding the mean velocity distribution and separation, comparison of experimental values with semiempirical relations, and wall shearing stress are provided.

Report presenting a method for driving time-response and frequency-response data for angle of attack and normal acceleration at the center of gravity of an aircraft when the data are measured at locations on the aircraft other than the center of gravity and when the pitching velocity is not measured.

From Introduction: "Flow and heat transfer in the entrance regions of channels have been subjects of considerable interest. The laminar flow case has been analyzed in references 1 (pp. 299-310), 2, and 3 (pp.451-464), for instance, and the turbulent case, in references 4 and 5."

From Introduction: "This report describes an experimental investigation of the use of a two-color electro-optical pyrometer as a means for measuring rapid changes in combustion temperatures."

Report presenting a graphical method for determining the motion of a freely oscillating system of one degree of freedom stabilized by a controlling device which applies control force in proportion to the displacement of the system, to its rate of change of displacement, or both.

Report presenting an investigation to create a design for fighter airplanes to have better inherent stability than most current designs. The main purpose of this design change is to obtain satisfactory stability of the Dutch roll oscillation without complicated artificial stabilizing devices. Results regarding the causes of inadequate dutch roll stability, means of improving dutch roll stability, and application of experimental design results to actual airplanes are provided.

Report presenting a method of calculating the deformations of wings of uniform thickness having swept M or W, upside down V, and swept-tip plan forms. The theory is modified and applied to more complex wing shapes as well as a simplified wing shape.