From summary: "This report covers an experimental investigation into the fabrication of various potential fuel-element materials and the testing of these materials for compatibility with structural metals at 1090 C (2000 F)."

From introduction: The results of U. S. Geological Survey exploration in the Legin group area are summarized briefly in this preliminary report. No additional drilling is planned. The Legin group area comprising nine Government-owned claims, three privately owned claims and adjoining public land, is in San Miguel County, Colo. The area explored includes parts of secs. 28 and 29, T. 43 N., R. 19 W., New Mexico principal meridian (fig. 1).

Abstract: Mesas 1 1/2 and II 1/2 were investigated in October 1951, to determine the extent and degree of uranium mineralization in the Salt Wash sandstone. Carnotite-vanoxite-type minerals are sufficiently concentrated to recommend 14,600 feet of drilling.

Report documenting the suitability of New Mexico for plant locations to produce synthetic liquid fuels, based on raw materials, water sources, and local interest

The purpose of the investigation reported herein was to develop data on the suitability of Prepakt concrete for mass concrete dams and for reinforced concrete construction. Prepakt concrete is made by packing the forms with coarse aggregate and then pumping in a cement base intrusion mixture (grout) to fill the voids.

Report issued by the U.S. Bureau of Mines on the production and use of various fuel and electrical energy types used in the U.S. during three census years: 1929, 1939, and 1947. The data is presented in multiple tables.

Report issued by the U.S. Bureau of Mines on the use of diesel fuel in the United States during 1951. 303 samples of diesel fuel are analyzed and recorded. This report includes tables and maps.

An experimental investigation of a highly loaded two-stage turbine with a downstream stator revealed that (1) at equivalent design work and speed the brake internal efficiency was 0.81 and the maximum efficiency obtained was 0.85, and (2) the downstream stator left very little energy in the form of tangential velocity in the gas and, in general, performed well with 0.78 recovery being obtained at equivalent design work and speed.

Note presenting the results of an investigation consisting of a series of one-engine climb tests with a twin-engine transport airplane, which indicate that light turbulence of the type generally present in clear air over flat terrain has no significant effect on the average rate of climb for a series of runs. Turbulence does, however, increase the variation in the rate of climb from run to run. Results regarding mean rate of climb, standard deviation of the rate of climb, effects of climb duration, and implications of these results are provided.

Report presenting four necessary conditions for steady irrotational compressible flow through a straight cascade of blades as derived from the irrotationality condition and conservation of mass and momentum. The expressions used can only give an approximate solution to the conditions, as there are an infinite number of them.

Note presenting an investigation to determine the effects of wing position and horizontal-tail position on the low-speed static longitudinal and static lateral stability characteristics of airplane models with unswept and 45 degree sweptback surfaces. The results indicated that both the unswept and sweptback low-wing low-horizontal-tail configurations were the optimum configurations from the standpoint of longitudinal and lateral stability.

Note presenting an investigation of the flow behind the attached curved shock near the nose of an axially symmetrical body placed in a uniform stream by considering the perturbations from the initial Taylor-Maccoll conical solution. Numerical results are obtained for the first-order perturbation equations, covering the cases with initial semivertex angle 10, 20 and 30 degrees, each at five different Mach numbers ranging approximately from the minimum one for an attached conical shock to a value around 5.

Note presenting a demonstration of the effect of axial and twisting misaligning couples on the oil film pressure distribution of a loaded bearing as shown by photographs of a number of three-dimensional plaster models representing averaged oil film pressure distribution under representative conditions. Five models with five different conditions were tested. Results regarding the oil film pressure distribution, bearing temperature distribution, and friction are provided.

From Introduction: "The present report is concerned with a closer investigation of the validity of this method and includes a more complete formulation, as well as the computation procedure, of the series expansion. As stated in reference 1, the flow thus determined depends only on the Mach number when the detached distance is adopted as the length scale. General formulas and the procedure of calculation are given in this report for such purposes."

Report presenting a study of the effect of rate of change of angle of attack on the maximum lift coefficient of a pursuit airplane equipped with a low-drag-type wing in stalls of varying abruptness over a range of Mach and Reynolds numbers. Maximum lift coefficients were found to increase linearly with increasing rate of change of angle of attack per chord length of travel up to the maximum rate attained in the tests.

Report presenting a method for predicting the upwash angles induced at the horizontal center line of the propeller disk of a particular twin-gate engine. The boundary conditions of the airship theory used to predict the upwash angles due to the nacelle of the airplanes was not strictly satisfied. Results regarding the evaluation of the method, application of the method to similar configurations, and extension of the method to dissimilar configurations are provided.

Note presenting an accurate method of determining secondary stresses in thin-walled, uniform beams of closed cross section. In the first part of the report, the integrodifferential equation governing axial displacements is formulated and solved for a beam without longitudinal stiffeners. In the second part, the corresponding summation-difference equation is developed and solved for a beam with stiffeners.

Report presenting a simplification of the Karman-Polhausen integral method as applied to compressible laminar boundary layers. The analysis was conducted under the assumptions of a Prandtl number of 1, zero heat transfer, and a linear viscosity-temperature relation.

Velocity and temperature profiles and laminar boundary-layer characteristics have been computed for Mach numbers from 1 to 10, utilizing experimental values of the heat capacity, viscosity, and conductivity. The analysis shows that effective temperature, which is a function of the surface temperature and stream conditions, arises naturally and is the proper reference temperature to be used in heat-transfer calculations. The effective temperature and the recovery temperature become identical for the condition of zero heat transfer.

From Summary: "The effects of ground interference on the aerodynamic characteristics of a 42 degrees sweptback wing have been determined at distances above the ground 0.68 and 0.92 of the mean aerodynamic chord (measured from the 0.25 mean aerodynamic chord). The wing was tested without flaps and with inboard trailing-edge split and outboard leading-edge flaps deflected. The wing had an aspect ratio of 4, a taper ratio of 0.625, and NACA 641-112 airfoil sections perpendicular to the 0.273 chord line. The results are, in general, comparable to those reported for unswept wings. The longitudinal stability at the stall was not materially affected at the ground heights of the present tests."

The "Busemann second-order-approximation theory" for the pressure distribution over a two-dimensional airfoil in supersonic flow was used to determine some of the aerodynamic characteristics of uncambered symmetrical parabolic and double-wedge airfoils with leading-edge and trailing-edge flaps. The characteristics presented and discussed in this paper are: flap effectiveness factor, rate of change of hinge-moment coefficient with flap deflection, rate of change of the pitching-moment coefficient with flap deflection, rate of change of the pitching-moment coefficient about the mid chord with flap deflection, and the location of the center of pressure of the airfoil-flap combination.

Procedure for pilot escape from spinning airplanes has been determined by means of tests in which pilot escape was simulated from 21 airplane models spinning in the Langley 20-foot free-spinning tunnel. The results in general indicated that the pilot should bail out of the outboard side. Calculated centripetal accelerations acting on the pilot during a spin are presented.

Results are presented of a wind-tunnel investigation made to determine the influence of the fuselage and tail surfaces on the rotary derivatives in yawing flight of a transonic-airplane configuration having 45 degrees sweptback wing and tail surfaces. The tests were run in the curved-flow test section of the Langley stability tunnel at a Reynolds number of 1.07 X 10 to the sixth power and consisted of balance measurements throughout the angle-of-attack range for several flight-path radii of curvature. The results are compared with data from forced-oscillation and free-oscillation tests, and a description of testing techniques used is included.

"The Poisson integral involved in the determination of the change in velocity distribution resulting from a change in airfoil profile in parallel incompressible flow is solved. First, three well-developed numerical methods of evaluating this integral, all based on the division of the range of integration into small equal intervals, and the difficulties involved in each method, are discussed. Then a new method, based on the use of unequal intervals, is developed, and compared with the other methods by means of several examples" (p. 1).