Memorandum presenting the results of an experimental investigation to determine the pressure-distribution characteristics of a conically cambered wing with and without pylon-mounted engine nacelles for Mach numbers of 1.6 and 1.9. The pressure data obtained during this investigation indicate that the low-pressure region existing on the upper surface over the forward part of the wing was spread over a larger proportion of the local chord than would be the case for an uncambered wing.

"Tests were made of a 1/18-scale dynamically similar model of the Lockheed Constellation airplane to investigate its ditching characteristics and proper ditching technique. Scale-strength bottoms were used to reproduce probable damage to the fuselage. The model was landed in calm water at the Langley tank no. 2 monorail. Various landing attitudes, speeds, and fuselage configurations were simulated" (p. 1).

Report presenting the effect of Mach number on the characteristics of the downwash and wake behind an unswept, tapered wing of aspect ratio 2.67 with full-span, 25-percent-chord, leading- and trailing-edge flaps has been determined from wind-tunnel tests. Results regarding downwash characteristics and wake characteristics are provided.

Report discussing a pressure-distribution investigation of a wing of a supersonic aircraft in the presence of a fuselage at a specified Mach number and aerodynamic chord. The wing had a quarter chord swept back 40 degrees, an aspect ratio of 4, a taper ratio of 0.5, and 10-percent-thick circular-arc sections perpendicular to the quarter-chord line. The results were compared to a similar investigation at a different Mach number.

Memorandum presenting a review of the current and anticipated lubricant problems as related to aircraft turbojet engines, which has indicated that the current and anticipated bearing operating temperature ranges to be met are specified. The most promising approaches, including types of lubricants and temperatures, are provided.

"Data on the aerodynamic excitation of first-order vibration occurring in a representative three-blade propeller having its thrust axis inclined to the airstream at angles of 0 degree, 4.55 degrees, and 9.80 degrees are included in this report. For several representative conditions the aerodynamic excitation has been computed and compared with the measured values. Blade stresses also were measured to permit the evaluation of the blade stress resulting from a given blade aerodynamic excitation" (p. 1111).

From Summary: "An investigation was made by the NACA wing-flow method to determine the drag, pitching-moment, lift, and angle-of-attack characteristics at transonic speeds of various configurations of a semispan model of an early configuration of the XF7U-1 tailless airplane. The results of the tests indicated that for the basic configuration with undeflected ailavator, the zero-lift drag rise occurred at a Mach number of about 0.85 and that about a five-fold increase in drag occurred through the transonic speed range. The results of the tests also indicated that the drag increment produced by -8.0 degrees deflection of the ailavator increased with increase in normal-force coefficient and was smaller at speeds above than at speeds below the drag rise."

The stall-limit line at low speeds was improved somewhat by closing the inlet guide vanes 6 deg, while the design-speed maximum flow and pressure ratio were reduced. The first-stage characteristic curve was moved to lower values of both flog coefficient and equivalent pressure ratio. The second-stage pressure ratio was decreased slightly at high speeds, while the later stages were unaffected.

Report presenting a large-scale diamond-wing-body configuration flown at a range of Mach and Reynolds numbers. The model had a diamond-plan-form wing with an NACA 65A003 airfoil section, a total aspect ratio of 2.31, and 0 degrees sweep of the midchord. Results regarding zero-lift drag and low-lift longitudinal characteristics are provided.

Memorandum presenting the results of an experimental investigation to determine the pressure-distribution characteristics of a conically cambered wing with and without pylon-mounted engine nacelles for Mach numbers of 1.6 and 1.9. Wing airfoil sections in the streamwise direction were composed of NACA 0004.08-63 sections symmetrically distributed about a cambered surface conical about the wing apex. Results regarding pressure distribution and loading are provided.

Memorandum presenting an investigation of the effect of Mach number variation from 1.8 to 7.4 on boundary-layer transition on a slender fin-stabilized ogive-cylinder body in free flight at a constant length Reynolds number of 13.8 million. Results showed that increasing Mach number had a very favorable effect of increasing the extent of the laminar boundary layer for a given surface roughness. Results regarding Mach number and surface roughness, effects of pressure rise, and long laminar runs are provided.

Memorandum presenting an investigation in the 9-inch supersonic tunnel to determine the effects of a sonic jet exhausting from a wing-mounted nacelle on the body drag of a body-wing-nacelle combination for various longitudinal, spanwise, and vertical nacelle locations and jet pressure ratios. The results indicated that the maximum variations in the total and fore drags of the body due to jet interference were about one-fourth of the basic body drag.

Report presenting an investigation made in the 4- by 4-foot supersonic pressure tunnel to determine the effects of body camber and body indentation on the longitudinal characteristics of a delta-wing-body combination at Mach number 1.61. Three bodies were tested with a 3-percent-thick 60 degree delta wing: a basic parabolic body, a body indented so as to have an improved wing-body area distribution at Mach number 1.8, and a body which was both indented and cambered. Results indicated that none of the changes had any appreciable effect at Mach number 1.61 on the minimum drag or maximum lift-drag ratios of the configurations tested.

"Flights to explore the high altitude and Mach number regions were made with the Douglas D-558-II research airplane in August 1951. Maximum pressure altitude recorded was 77,500 feet and the maximum geometric altitude obtained from radar data was 79,500 feet above sea level. The maximum Mach number obtained was 1.87. When a standard atmosphere is assumed, this value represents a true airspeed of 1238 miles per hour; or at the existing temperature, 3 degrees Fahrenheit above standard, this represents an airspeed of 1243 miles per hour" (p. 1).

"Two experiments concerning the transonic area rule have shown that the wing of a configuration has a powerful effect as a dividing plate. The approximation of store plus interference wave drag (near a Mach number of 1) for underwing stores was more accurately made by considering the normal area development of the configuration above and below the wing separately instead of the total area development. Indenting a fuselage on only one side of the wing to allow for the exposed wing volume gave appreciably less pressure-drag reduction than that obtained with a symmetrically indented fuselage" (p. 1).

"A solution to second order in thickness is derived for harmonically oscillating two-dimensional airfoils in supersonic flow. For slow oscillations of an arbitrary profile, the result is found as a series including the third power of frequency. For arbitrary frequencies, the method of solution for any specific profile is indicated, and the explicit solution derived for a single wedge" (p. 611).

Document issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, John Ben Shepperd, regarding a legal question submitted for clarification: Authority of the Bureau of Labor Statistics to license a Grayson County resident to operate an employment agency in Jefferson County.

Document issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, John Ben Shepperd, regarding a legal question submitted for clarification: Legality of the county attorney accepting private employment to maintain an injunction action adverse to the collection of certain taxes by an independent school district.

Document issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, Will Wilson, regarding a legal question submitted for clarification: Whether Navarro County can spend tax money to maintain dams constructed in Navarro County by the Navarro-Hill Soil Conservation District.

Document issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, Will Wilson, regarding a legal question submitted for clarification: Constitutionality of H.B. 57, 56 Leg., relating to whether or not the State may tax beer sold to and consumed on Military Reservations within the State.

Document issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, Will Wilson, regarding a legal question submitted for clarification: Constitutionality of House Bill 102, 56th Leg., The Texas Area Planning Act.

Letter opinion issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, John Ben Shepperd, regarding a legal question submitted for clarification; Payment of County Attorney's commissions, when criminal judgements are paid, to the incumbent County Attorney or to the person who was County Attorney when the judgement was entered.

Ion exchange column elution methods for the separation of americium and curium using tartrate and lactate solutions have been developed which are superior to citrate elutions. Tartrate elutions are suitable for slow separations and lactate elutions are satisfactory for general use where rapid separations are required. Fission and spallation products were isolated from Pu{sup 239} targets which had been bombarded with alpha particles of 21 to 37 Mev energy. Fission yield curves as well as fission and spallation excitation functions are presented and discussed in terms of odd-even and Z{sup 2}/A effects. The high cross sections observed for the (a, 2n) and (a, p2n) reactions were surprising results from this investigation. In the course of the Pu{sup 239} bombardments, studies of the decay schemes of Am{sup 240}, Cm{sup 240}, and Cm{sup 241} were undertaken. Decay energy and half-1ife information on all of the transmercury nuclides has been collected and systematized. Trends on the energy surface for alpha energies, beta energies, nucleon binding energies, and Bohr-Wheeler parameters are presented. These energy systematics have led to a complete tabulation of the masses of the isotopes of the elements above mercury. Predictions of nuclear properties are included for some isotopes of elements 99 …

BS>The thermal characteristics of various reactors fueled with uranium dioxide fuel pellets are listed. (W.L.H.)