The report summarizes source material on combustion for flight-propulsion engineers. First, several chapters review fundamental processes such as fuel-air mixture preparation, gas flow and mixing, flammability and ignition, flame propagation in both homogenous and heterogenous media, flame stabilization, combustion oscillations, and smoke and carbon formation. The practical significance and the relation of these processes to theory are presented. A second series of chapters describes the observed performance and design problems of engine combustors of the principal types. An attempt is made to interpret performance in terms of the fundamental processes and theories previously reviewed. Third, the design of high-speed combustion systems is discussed. Combustor design principles that can be established from basic considerations and from experience with actual combustors are described. Finally, future requirements for aircraft engine combustion systems are examined.

"Tests have been conducted in the Langley 8-foot transonic tunnel on a 0.04956-scale model of the Convair F-102A airplane which employed an indented and extended fuselage, cambered wing leading edges, and deflected wing tips. Force and moment characteristics were obtained for Mach numbers from 0.60 to 1.135 at angles of attack up to 20 degrees. In addition, tests were made over a limited angle-of-attack range to determine the effects of the cambered leading edges, deflected tips, and a nose section with a smooth area distribution" (p. 1).

From Introduction: "Numerous tests of tip controls on delta wings at transonic and low supersonic speeds have shown that such configurations provide satisfactory rolling-moment effectiveness, and that the hinge can be controlled by proper location of the hinge line (ref. 1). The purpose of the present tests is to determine the characteristics of such a configuration at Mach number of 4.04 and a Reynolds number of 5.8 X 10^6, based on the wing mean aerodynamic chord."

This report contains the results of tests which demonstrated the feasibility of using graphite labyrinth type seals, i.e., a bushing machined with alternate grooves and lands on the inside diameter to create a sufficient pressure drop to provide a satisfactory seal.

From Introduction: "The purpose of the present report is to present a comprehensive summary of theoretical investigations of comprehensible laminar boundary layers which have been carried out since 1949 at the Polytechnic Institute of Brooklyn under the sponsorship and with the financial assistance of the National Advisory Committee for Aeronautics. The results of these investigations are contained primarily in references 1 to 7."

From Introduction: "In rounded-approach nozzles with discharge coefficients close to unity, the frictional effects are concentrated in the boundary layer. A method of obtaining an analytical relation among the discharge coefficient, Reynolds number, and the nozzle geometry by utilization of elementary boundary-layer theory is presented herein."

Report describing the angular distributions of several groups of charged particles resulting from the bombardment of carbon with 31-Mev protons.

The report describes a brief review is made of improvements to an experimental apparatus for time and space correlation designed for study of turbulence. Included is a description of the control of the measurements and a few particular applications.

The generalized shock-expansion method is applied to obtain solutions to the flow field about pointed bodies of revolution at high supersonic airspeeds and small angles of attack. Simple explicit expressions are obtained for the surface Mach numbers and surface pressures in the special case of slender bodies. In the case of inclined cones, algebraic solutions are obtained defining the entire flow field. Experimental pressure-distribution data for cones and ogives at Mach numbers from 3 to 5 are included. (author).

The Reactor Design and Development Unit has just completed a design concept for an intermediate capacity dual purpose reactor plant utilizing carbon steel for the primary loop portion outside the reactor. This design concept is reported in HW-33157 AD (2). The economic and engineering gains are of sufficient magnitude to justify an accelerated and extensive test program to completely evaluate the remaining unknowns in utilizing carbon steel as a stainless steel substitute. It is the purpose of this document to up-date and elaborate the information contained in the two previous documents (1). . It is the further purpose to define the program required to implement the design concept developed by the Reactor Design and Development Unit (2) utilizing carbon steel as the primary loop structural material.

Attached hereto are copies 1 through 4 of a classified secret report titled "Purex - A Hanford Separations Plant." We are also sending under separate cover a classified confidential report No. HW-36496 titled "Photographs of Purex - A Hanford Separations Plant," which is a counterpart of the above report. These documents are submitted for publication and should be incorporated as a single article.

Note presenting flight tests on a twin-engine transport airplane to determine the effects of fuselage-nacelle interference on the circumferential distribution of the rise in total pressure at one radial station behind the propellers. The effects of the flow interference on the operation of a simple propeller-thrust indicator are investigated. Results regarding the effect of airspeed at full power, effect of wing flaps in approach condition, effect of power in cruise condition, effect of angle of yaw in the cruise condition, effect of engine cowl flaps in the approach condition, and thrustmeter-tube locations are provided.

Memorandum presenting a force-test investigation to determine whether the static stability characteristics of a twisted and cambered 68.7 degree delta wing could be approximated by a plane wing of similar plan form with dihedral. Results regarding longitudinal characteristics and lateral characteristics are provided.

Report comparing two methods for converting from grain counts to weight percent composition. One method uses the concept of average weight per grain of each mineral, and the other uses a specific gravity factor method.

Memorandum presenting an investigation of the compressor and turbine operating trends during acceleration and deceleration of two hypothetical two-spool turbojet engines. The two engines have the same component performance maps but the arbitrarily specified ratio of outer- to inner-spool moment of inertia for the second engine is 4 times that specified for the first engine. Results regarding the acceleration characteristics and deceleration characteristics are provided.

Report presenting an approximate method for the calculation of the compressible laminar boundary layer with heat transfer and arbitrary pressure gradient, based on Thwaites' correlation concept. The method results from the application of Stewartson's transformation to Prandtl's equations, which yields a nonlinear set of two first-order differential equations. Calculations of an example show that the method is reliable when compared with the perturbation method over the same range of Mach number, pressure gradient, and heat transfer.

Report discussing new cell dimensions, space groups, specific gravity determinations, and number of formula units per cell for uranyl vanadates, phosphates, and arsenates.

Note presenting extensive data relating properties of wrought N-155 alloy under static, combined static and dynamic, and completed reversed dynamic stress conditions. Time periods for fracture ranged from 50 to 500 hours at room temperatrue, 1000, 1200, 1350, and 1500 degrees Fahrenheit. Results regarding the rupture and fatigue strengths, fatigue strengths based on cycles to failure, influence of superimposed fatigue loads on creep, influence on superimposed fatigue stress on elongation in the rupture test, stress-strain characteristics under fatigue loading, damping effects, influence of cyclic speed on fatigue properties, influence of notches on fatigue, surface finish, and limitations of findings are provided.

Report presenting an analysis of losses occurring in a series of subsonic turbine blades in a low-speed two-dimensional cascade and in a related series of four transonic rotors. Results regarding the two-dimensional cascade loss correlations, transonic turbine loss correlations, effect of unsteady flows, and mixing of stator wakes are provided.

Report presenting performance testing of a supersonic compressor designed for a tip speed of 1400 feet per second, a pressure ratio of 2.0, and a corrected weight flow of 30.5 pounds per second. The overall performance results of the rotor alone at design speed gave a pressure ratio of 2.17, an adiabatic efficiency of 89 percent, and a weight flow of 28 pounds per second. A comparison with the predicted design results is provided.

Report presenting the results of an analytical and experimental investigation of the steady-state and dynamic characteristics of three types of throttle-controlled fuel systems. The three systems tested are a throttle with regulated upstream pressure, a throttle plus bypass differential-pressure regulator, and a throttle plus reducing-valve differential-pressure regulator with regulated supply pressure. Results regarding the effect of output pressure on the controlled flow, response of output flow to step changes in throttle area, and response of output flow to a sinusoidal variation in throttle area are provided.

From abstract: "A method is presented for the separation and spectrophotometric determination of thorium in zircon and other associated minerals... The steps necessary for the separation of interfering ions are discussed, and a study of the effect of various cations and anions is presented."

The purpose of this work was to produce a reliable, inexpensive instrument for the detection of hard beta contamination on the clothing of personnel. Also, the monitoring was required to be accomplished without interrupting the normal activities of the employees.

Report presenting an investigation of the pressure limits of flame propagation for isooctane, ammonia, and mixtures of the two in air at a range of temperatures. A hot-wire ignition source was used and testing occurred in a 2-inch-diameter flame tube that was closed at both ends. For all mixtures studied, the rich limit rose considerably and the lean limit decreased slightly when temperature was raised.