Report presenting an investigation at low speed to determine the static aerodynamic forces and moments on a canard missile model during launching from the midsemispan and wing-tip locations of a wing-fuselage combination with a 45 degree sweptback wing. When the missile was mounted under the wing at the midsemispan location, changes in chordwise position produced large changes in missile forces and moments.

Introduction: This is the fifth of a series of reports covering technical progress on the research and development program being performed in connection with the design of the Pathfinder Atomic Power Plant.

It is recommended that self-concentration of Purex wastes should not be started until much more complete knowledge is obtained of the conditions and reactions in these wastes. The presently planned tests in the Semi-Works will be a practical demonstration of the problems but will be of little value on the initial Purex wastes as these tests are being run almost concurrent with the filling of the first Purex storage tank.

Thus we see that the derivation of elementary age theory is based on replacing the probability of collision governed by the Milne kernel by a Gaussian probability having the same zeroth and second moments. It is apparent that the age theory distribution will fail close to the source and at many free paths from the source.

Note presenting the problem of the effect of yaw on the turbulent boundary layer and skin friction of infinite cylinders, which is reviewed and compared with the case of laminar flow. The conclusion indicates that present understanding of the mechanism of turbulent shear does not permit exhaustion of two-dimensional data even to this elementary case of three-dimensional flow. Results regarding pressure distributions, two-dimensionality and flow direction, velocity profiles, virtual origin, virtual origin for yawed plates, boundary-layer growth, and the results obtained by Young and Booth are provided.

Report presenting testing on a 60 degree delta-wing XF-92A airplane at a variety of Mach numbers to obtain measurements regarding buffet-induced fluctuations in normal acceleration and of fluctuations in structural shear load of the left wing. The altitudes tested ranged from 25,000 to 38,000 feet. Results regarding the buffet boundary, wing flow conditions, buffet frequencies, buffet intensities, and a comparison to buffeting of other airplanes are provided.

Report presenting a flight investigation over a range of altitudes and lift to determine the wing loads of the Bell X-5 research airplane at a sweep angle of 58.7 degrees at subsonic and transonic Mach numbers. Testing indicated that wing loads exhibit nonlinear trends over the angle-of-attack range from zero to maximum wing lift.

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.

Data obtained from the first flight test of a ram jet utilizing a magnesium slurry fuel are presented. The ram jet accelerated from a Mach number of 1.75 to a Mach number of 3.48 in 15.5 seconds. During this period a maximum values of air specific impulse and gross thrust coefficient were calculated to be 151 seconds and 0.658, respectively. The rocket gas generator used as a fuel-pumping system operated successfully.

Report presenting the results of oscillation tests to measure the dynamic-rotary stability derivatives of an airplane model at high subsonic speeds. Measurements taken included the damping in pitch, damping in yaw, damping in roll, and the yawing moment due to rolling velocity.

A principle for bending crystals with a minimum of strain so that they will focus x-rays and gamma-rays accurately to a point is explained. Detailed calculations are made of the aberrations in the foci resulting from various applications of the principle. the application of the principle in making a point focusing monochromator for low angle x-ray diffraction studies is discussed, and theoretical and experimental determinations of the reflection coefficient of the crystal are compared. A few experiments in low angle diffraction from biological materials using the new monochromator are described, and the results are compared with those obtained using other instruments.

Report presenting a program to investigate the aerodynamic characteristics of thin delta wings with symmetrical double-wedge sections in the hypersonic tunnel at a Mach number of 6.9. A family of 5-percent-thick lifting wings with semiapex angles were tested over a range of angles of attack. Results regarding lift and drag characteristics, center of pressure and moment coefficient, Schileren photographs, and surface film flow studies are provided.

From Summary: "The results of force tests made at low speed are presented to show the effect of longitudinal static stability produced by drooping the tip of a 63 degree sweptback wing. Five semispan wing models were tested: two incorporated curved drooped tips, two with abruptly drooped tips, and one without droop. The most favorable stability characteristics were measured for a model with an abruptly drooped tip, a fence, and a leading-edge flap; however, the use of these same auxiliary devices on the undrooped wing was nearly as effective."

Report presenting a scale rocket-propelled model of the Convair XF2Y-1 water-based fighter airplane in free flight in a range of Mach numbers. Results regarding stability characteristics, trim characteristics, drag characteristics, and inlet and duct characteristics are provided.

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Report presenting testing of several configurations of rotor blades in order to evaluate the effect of variations in the blade-pitch-control stiffness and forward speed on the flutter speed.

Report presenting the slender-body approximation of linearized compressible flow as applied to the problem of a delta wing in which flow separation occurs at the leading edges. Leading-edge separation was found to produce an increase in lift over that given by the Jones slender-wing theory and that lift does not linearly increase with angle of attack.

This report is a compilation of 48 investigator prepared summaries of recent progress in individual research programs of the Biology and Medical Division of the Argonne National Laboratory for the quarterly period ending April,1955. Individual reports are about 3-6 pages in length and often contain research data.

From Summary: "Trajectories of water droplets about an ellipsoid of revolution with a fineness ratio of 10 (10 percent thick) in flight through a droplet field were computed with the aid of a differential analyzer. Analyses of these trajectories indicate that the local concentration of liquid water at various points about an ellipsoid varies considerably and under some conditions may be several times the free-stream concentration. Curves of the local concentration factor as a function of spatial position were obtained and are presented in terms of dimensionless parameters that describe flight and atmospheric conditions."

The purpose of this course is two-fold. It should serve as a review for the metallurgist of the classical metallurgical concepts applied to such metals as uranium, thorium, plutonium, and zirconium. These metals are relatively unfamiliar to the metallurgist, but the concepts are still the same ones applied to familiar metals. The second purpose is to acquaint the non-metallurgist with the reasons for selection, advantages, and disadvantages of the various fuels and structural materials used in a reactor. Thus, there are two purposes: the first is conceptual, and the second is explanatory. A blending of the two must inevitably result in an over-simplification of the metallurgical concepts and an assumption of certain background material which, actually, may not be available to the non-metallurgist. The present lecture is an introduction to the material to be covered. This lecture will have two purposes. The material to be presented in the remaining lectures will be outlined briefly, and the various concepts to be covered in this course will be discussed.

Memorandum presenting the effects on combustor performance of operation at the high inlet-air pressures, temperatures, and velocities representative of conditions that may be encountered in high-pressure-ratio turbojet engines or at high flight speeds studied in a single tubular combustor. Some of the performance characteristics investigated were combustor-liner temperatures, carbon deposition, smoke formation, and combustion efficiency.

The preparation, pre-irradiation testing, and encapsulation of stainless- U cored, plate-type fuel elements for irradiation in;tagnant sodium are discussed The eight specimens for Experiment PW-5-1 are examined. (auth)

Report presenting a blade-vibration and rotating-stall survey on a production turbojet engine with a 13-stage axial-flow compressor with a pressure ratio of 7 and an air flow of 120 pounds per second. Results regarding stall patterns, maximum vibratory stresses, and location of the stall zones are provided.