From Introduction: "Data are presented to show the effects of tail-pipe fuel-air ratio, altitude, and flight Mach number on tail-pipe-burner performance at rated engine speed and approximately constant turbine-outlet temperature. Operational characteristics of the tail-pipe burner and variable-area exhaust nozzle are also reported."

Analytical methods are presented for the determination of local values of outside and inside heat-transfer coefficients and effective gas temperatures by use of turbine-blade-temperature measurements. The methods are derived for a number of configurations that can be applied to typical cooled-turbine-blade shapes as well as to other types of heat-transfer apparatus.

An equation for average heat transfer of a surface was derived when the boundary layer changed from laminar to turbulent. Influences on the heat transfer through a laminar boundary layer of Mach number, temperature ratio (gas temperature divided by wall temperature), and exponents of gas-property temperature relations were shown to be relatively small for air with Mach numbers less than 2 and temperature ratios between 1 and 4. Good agreement was obtained with experimental results from cylinders, an airfoil, and turbine blades.

From Introduction: "Analyses of heat transfer for liquid metals flowing turbulently in smooth tubes (low Pradtl numbers) are given in reference 1 and 2. The predicted heat-transfer coefficients from these analyses are considerably higher than those determined in the experimental heat-transfer investigations for mercury and lead bismuth given in references 2 to 4. If the analytical and experimental results for flow of gases are compared at low Peclet numbers, they are also found to be in disagreement (references 5 and 6)."

Performance characteristics of a two-dimensional isentropic diffuser have been experimentally determined at a Mach number of 3.85. At zero angle of attack, a maximum total-pressure recovery of 0.41 was obtained with a supercritical mass-flow ratio of 0.95. As a consequence of the twin-duct arrangement of the diffuser, a large discontinuity in pressure recovery and mass flow with a characteristic hysteresis was encountered between critical and subcritical operation. An asymmetric shock pattern with large-scale separation and flow reversal in one of the passages occurred at reduced mass flows. Pressure and force data presented for an angle-of-attack range from zero to 4 degrees.

"This symposium is concerned with the basic aspects of radiation effects. When we turn to the genetic effects of radiation in mammals, there are so few aspects on which there is any information that the problem of sorting out the fundamental findings has hardly arisen. In this paper it will, therefore, be possible to survey most of what is known and pass on to a consideration of what is needed next. Since one of the purposes of this symposium is an interchange of views between investigators in different fields, an attempt will be made to avoid technical details. Among the practical needs in mammalian radiation genetics is a pressing one for more data on which to base estimates of the genetic hazards of radiation in man. The present paper will be concerned largely with this problem. Our own work is directed primarily in this direction, our objective being to uncover some of the basic facts in at least one mammal-the mouse. Before discussing the experimental work, however, it seems desirable to consider some of the general features of the genetic hazard of radiation."

Memorandum presenting minimum spark-ignition engines at reduced pressures for ethane, ethylene, acetylene, n-hexane, cyclohexane, and benzene.

"Paper presents a practical method for computing the approximate values of the normal component of the induced velocity at points in the flow field of a lifting rotor. Tables and graphs of the relative magnitudes of the normal component of the induced velocity are given for selected points in the longitudinal plane of symmetry of the rotor and on the lateral rotor axis. A method is also presented for utilizing the tables and graphs to determine the interference induced velocities arising from the second rotor of a tandem or side-by-side-rotor helicopter and the induced flow angle at a horizontal tail plane" (p. 1).

Control requirements were determined from calculated engine performance maps for a fixed-geometry ram jet of a configuration suitable for strategic supersonic missile propulsion. Several control schemes for attaining desired engine performance and for stabilizing missile flight velocity during cruise are presented. The advantages and disadvantages of each system are discussed.

Seven runs were made with the system Penn. Ref. Co. "Supersol" (dispersed) water (continuous) to investigate the effects of pulse frequency, amplitude plate spacing, volume flow ratio, and throughput on backmixing, using the technique of continuous injection of a tracer solution into the packed section. Backmixing was found to be surprisingly insensitive to all the above variables over the range studied with the exception of pulse amplitude and continuous phase flow rate, showing greatest dependence on the later. Backmixing increased with decreasing continuous phase flow rate and increased with pulse amplitude.

Report issued by the Argonne National Laboratory discussing engineering properties of diphenyl. As stated in the abstract, "data collected from the literature on the vapor pressure, enthalpy, liquid density, and vapor density of pure diphenyl are presented. A Mollier diagram, a temperature entropy diagram, and data on viscosity of diphenyl as a function of temperature are also presented" (p. 5). This report includes tables, and illustrations.

Abstract: The number of photons of given energy radiated in Bremsstrahlung collision of electrons with nuclei is calculated relativistically. Expansions are obtained for energies small to mc-squared. The photon spectrum is averaged over a Maxwell distribution for the electrons. Numerical results are included.

Report presenting a Bendix-Friez Aerovane Anenometer oscillated in the streamwise direction at several frequencies for each of several low wind-tunnel airspeeds. Records of the displacement of the anenometer and velocity indicated by the instrument during oscillation are provided. The over-registration of this anenometer was found to be much smaller than predicted by theory.

Experiments are described which show that magnetic fields can exert a controlling influence on the operating characteristics of point contact transistors. The effect is especially evident when the transistor is operated in its negative resistance region. The frequency of an oscillator can be varied, or a switch made to trigger by applying a magnetic field to the transistor. Some applications of the principle are suggested; many more are evident.

The longitudinal stability and control characteristics of a 1/30-scale model of the Republic XF-103 airplane were investigated in the Langley 8-foot transonic tunnel. The effect of speed brakes located at the end of the fuselage was also investigated. The main part of the investigation was made with internal flow in the model, but some data were obtained with no internal flow. The longitudinal stability and control at transonic-speeds appeared satisfactory. The transonic drag rise was small. The speed brakes had no adverse effects on longitudinal stability.

Abstract: "The cross section for the reaction Al²⁷(p,3pn)Na²⁴ has been measured for proton energies between 30 and 350 Mev relative to the cross section for the reaction C12(p,3pn)C11, and the absolute magnitude determined by matching with data measured with a Faraday cup at 350 Mev and at 31.5 Mev."

From Introduction: "The importance of blunt noses as a means of reducing the heat transfer to high velocity missiles has recently received much publicity. The question of just what blunt shape is best is still moot, and it is the purpose of this paper to present and examine some recent experimental results which may throw some light on this problem."

From Introduction: "The importance of blunt noses as a means of reducing the heat transfer to high velocity missiles has recently received much publicity. The question of just what blunt shape is best is still moot, and it is the purpose of this paper to present and examine some recent experimental results which may throw some light on the problem."

Abstract: "Fabrication techniques for making metal-ceramic fuel elements containing 60 to 90 volume per cent of UN or UO2 in a Type 302B stainless steel matrix was investigated. A hot press-forging procedure was most successful for fabricating fuel cores with a density of 90 per cent of theoretical or better. This procedure consisted of sealing the cold-pressed core compacts in stainless steel picture-frame packs, heating to 1900 F, and pressing to a total reduction in thickness of 35 per cent. A pressure of approximately 50 tsi ores used. Specimens produced by this method were evaluated on the basis of their microstructure, modules if rupture, electrical conductivity, and resistance to thermal shock. Microscopic and macroscopic examination showed the presence of a continuous metal skeleton even in specimens containing 90 volume per cent fuel. The modulus of rupture at room temperature varied from 22,500 psi for a specimen cnotaining 63 volume per cent UO2. Both the electrical conductivity and resistance to thermal shock of UO2 were improved by the addition of a small volume of metal. Gas-pressure-bonding techniques appear promising for clodding these cores into composite elements."

Report presenting the tracking performance of an automatically controlled interceptor in which the deflection channel incorporated a bank-angle-error computer that commanded rolling velocities of the interceptor proportional to the computed bank-angle errors. Results regarding gravity terms included in bank-angle-error computation and a comparison of modified system using bank-angle-error computer with the prototype system are provided.

Report discussing various features of the stability of ballistic reentry shapes, including considerations for ballistic-missile and manned-satellite reentry capsules. Attainment of satisfactory stability of reentry bodies with subsonic terminal velocities was not found to be too difficult, but undesirable features that may cause marginal stability characteristics may be introduced in an effort to minimize weight. Reentry bodies with supersonic terminal velocities have fewer stability issues.

Report presenting a 45 degree sweptback wing of aspect ratio 3, with twist and a distributed type of camber, tested in combination with a body of fineness ratio 12.5 to determine the lift, drag, and pitching-moment characteristics.

A program has been prepared for the 709 computer which will determine extrapolation length from horizontal traverses measurements taken in an exponential pile. The flux across the pile is assured to fit a cosine function of the form y = A cos B (X-C)

Abstract: "This paper describes an electrical readout, decade counter employing the magnetron beam switching tube with transistor drive. Double pulse resolution is one microsecond. The unit will accept a variety of transistor types and will tolerate supply voltage variations of +/- 20% at ambient temperatures up to 60 C. A "Pixie" neon indicator is driven without the use of additional transistors. A readout circuit for printer on punched paper tape is presented."