This paper includes the following topics: 1) Characteristic differential equations; 2) Treatment of practical examples; 3) First example: Diffuser; and 4) Second Example: Nozzle.

Contents include the following: Characteristic differential equations - initial and boundary conditions. Integration of the second characteristic differential equations. Direct application of Meyer's characteristic hodograph table for construction of two-dimensional potential flows. Prandtl-Busemann method. Development of the pressure variation for small deflection angles. Numerical table: relation between deflection, pressure, velocity, mach number and mach angle for isentropic changes of state according to Prandtl-Meyer for air (k = 1.405). References.

Report providing an alphabetical listing of the periodicals, both American and foreign, that are currently being received in the Washington (D.C.) Library of the National Bureau of Standards. Approximately 2,000 titles are cited, together with call numbers indicating the location of each in the NBS Washington Library. Although this information was compiled primarily for the use of the Bureau's scientific staff, it is also of value to libraries, scientific and technical organizations, and research workers.

Report discussing testing on a series of tapered swept wings under conditions simulating rolling flight. The lift, longitudinal-force, and pitching-moment characteristics for three swept wings are provided. The results indicated that a decrease in taper ratio on a swept wing caused a small decrease in damping in roll at low and moderate lift coefficients.

Report presenting an investigation of a 45 degree sweptback-wing model with interchangeable round and sharp leading edges to determine the effect of leading-edge separation on the loads experienced by the models in gusts. Leading-edge separation was found to increase the gust load, which appeared to vary based on the gust-gradient distance and velocity.

Report presenting an experimental investigation to determine the vibration characteristics of loosely mounted turbine blades during service operation of a turbojet engine. High-temperature strain gages were used to measure turbine-blade vibrations. Results regarding oscillograph records, critical speeds and frequencies, vibratory-stress levels, and effect of tightening the blade mount are provided.

Report presenting an investigation in the stability tunnel to determine the effect of airfoil profile on symmetrical sections on the static- and yawing-stability derivatives of three untapered wings of 45 degrees sweepback. All of the wings had an aspect ratio of 2.61. Results regarding the characteristics in straight flow, yawing flow, and drag index are provided.

Contains results of tunnel tests to determine effects of various combinations of split flaps, slats, and nose slats on the stability characteristics of a tapered 37.5 degree sweptback wing of aspect ratio 3 in straight and rolling flow.

From Summary: "An air-launched cone-cylinder test vehicle designed to obtain data at Mach numbers above 4.0 was rocket boosted from a release Mach number of 5.18. The vehicle was launched at an altitude of 35,000 feet and reached peak velocity of 5150 feet per second at 28,500 feet. The total-drag coefficient (based on maximum cross-sectional area) decreased gradually from 0.31 at a Mach number of 1.75 to 0.145 at a Mach number of 5.18, while the Reynold's number (based on body length) increased from 31 x 10 to the 6th power to 107 x 10 to the 6th power."

Report presenting an investigation of the low-speed characteristics of a 25-foot span triangular wing with an aspect ratio of 2. the airfoil section of the wing was a symmetrical double wedge with 5-percent maximum thickness at 20-percent chord. Results regarding the longitudinal characteristics, lateral characteristics, and directional characteristics are provided.

Report presenting a wind-tunnel investigation performed at low speed to determine the aerodynamic characteristics of a 51.3 degree sweptback semispan wing equipped with 16.7-percent-chord plain flaps and ailerons with various spans and spanwise locations and one with span of aileron with trailing-edge angles of 6, 14, and 25 degrees. Results regarding the wing aerodynamic characteristics, aileron-control characteristics, spoiler control characteristics, and effect of wing-tip shape are provided.

Final report documenting a high-sensitivity airborne radiometric and magnetic survey of the Newark quadrangles including the survey description, specifications, data processing methods, interpretation methods, and regional geologic review.

Partial abstract: "The objective of the investigation reported herein was to obtain laboratory response data for deep, two-way-reinforced and plain concrete slabs subjected to static overpressures in order to determine the response analysis necessary to analyze the target vulnerability of such structures under both active and passive defense situations" (p. 4).

From Introduction: "Uranium has been discovered in fluvial quartz-pebble conglomerates in most of the Precambrian shield areas of the world, including the Canadian, African, South America, Indian, Baltic, and Australian shields. Occurrences in these and other areas are shown in Figure 1.1. Two of these occurrences, the Huronian supergroup of Canada and the Witwatersrand deposit of South Africa contain 20-30 percent of the planet's known uranium reserves (Nininger, 1974). Thus it is critical that we understand the origin of these deposits and develop exploration models that can aid in finding new deposits."