From Introduction: "The purpose of this paper is to review new and significant data which will be of interest to designers in determining the heating of these components. A comparison with existing theory to indicate its adequacy in each case is also presented."

"An investigation has been completed in the Langley 20-foot free-spinning tunnel on a 1/24-scale model of the Grumman F11F-1 airplane to determine its spin and recovery characteristics. An interim report, Research Memorandum SL55G20, was published earlier and the present report concludes the presentation of results of the investigation. Primarily, the present report presents results obtained with engine gyroscopic moments simulated on the model. Also, the current results were obtained with a revised larger vertical tail recently incorporated on the airplane" (p. 1).

Report presenting an experimental investigation to determine the effect of boundary-layer control and inlet lip shape on the performance of a side-inlet air-induction system for a fighter-type airplane. Two methods of boundary layer control and three inlet lip shapes were investigated at a range of Mach numbers and mass-flow ratios. Results regarding net propulsive thrust are also provided.

From Summary: "Lateral-stability flight tests were made over the Mach number range from 0.7 to 1.3 of models of three airplane configurations having 45 degree sweptback wings. One model had a high wing; one, a low wing; and one, a high wing with cathedral. The models were otherwise identical. The lateral oscillations of the models resulting from intermittent yawing disturbances were interpreted in terms of full-scale airplane flying qualities and were further analyzed by the time-vector method to obtain values of the lateral stability derivatives."

Abstract: "This report describes six electronics areas at the Radiation Laboratory (Berkeley and Livermore) that are being successfully used with various particle acceleration for nuclear research. The electronics equipment, consisting of pulse amplifiers, scalers, coincidence circuits, pulse-height analyzers, automatic recording equipment, high-voltage supplies, etc., is arranged in such a manner that most experiments can be quickly set up, and a number of people can run experiments simultaneously. Advantage and limitations of these areas are discussed."

Report presenting testing of a series of single and double unswept, lateral-support struts at a Mach number of 1.9 on a cone-cylinder body at zero angle of attack. The struts consisted of a rectangular box section with identical wedge fairings fore and aft. Results regarding the shock-wave intersections and pressure distributions are provided.

It was shown that without further major development the detectors proposed for the Body Monitor can be expected to detect 0.02 microcurie of plutonium at the center of the chest cavity. This is the permissible body burden of insoluble forms of plutonium. The detection level can be decreased by decreasing the background counting rate. Decreases in the background can reasonably be expected; it should be possible to detect a small fraction of the permissible body burden. If it can be shown, as suggested by other work, that americium will remain with plutonium, then within at least a few months after entry into the body it should be possible to measure the plutonium by detection of rays from Am²⁴¹.

The purpose of this report is to provide data pertaining to the corrosion damage incurred in the use of oxalic acid as a cleaning agent for process equipment.

Report presenting an investigation of the F9F-4 airplane to evaluate a high-energy blowing boundary-layer-system in flight in order to improve the maximum lift characteristics of airplane wings. A high-energy blowing-boundary-layer control system was installed by the Grumman Aircraft Engineering Corporation. A series of test flights were made to measure the lift and drag variations with changes in angle of attack for the flap and gear both up and down and for blowing on and off.

Report presenting an investigation of the handling qualities of a fighter airplane that is controlled by a pilot supplying signals to a rate type of automatic control system. The handling qualities were investigated in pull-ups, aileron rolls, aerobatics, rough-air flying, and precision tasks.

Gas pressurization of homogeneous reactor test results.

Report presenting gas-to-blade heat-transfer coefficients and turbine heat-rejection rates obtained for a wide range of one-spool turbojet engine designs believed to be representative of engines that will employ turbine cooling. The values of heat-transfer coefficient and heat-rejection rates are applicable to both liquid- and air-cooled turbines. Results regarding the heat-transfer coefficients and heat-rejection rates for turbojet engine designs, total heat-rejection rates for various turbojet engine and flight conditions, and heat-transfer coefficients and heat-rejection rates for turboprop engine design are provided.

From Summary: "Heating requirements for satisfactory cyclic de-icing over a wide range of icing and operating conditions have been determined for a gas-heated, 36 degree swept airfoil of 6.9-foot chord with a partial-span leading-edge slat. Comparisons of heating requirements and effectiveness were made between the slatted and unslatted portions of the airfoil. Studies were also made comparing cyclic de-icing with continuous anti-icing, and cyclic de-icing systems with and without leading-edge ice-free parting strips. De-icing heat requirements were approximately the same with either heated or unheated parting strips because of the aerodynamic effects of the 36 degrees sweep angle and the spanwise saw-tooth profile of leading-edge glaze-ice deposits. Cyclic de-icing heat-source requirements were found to be one-fourth or less of the heat requirements for complete anti-icing. The primary factors that affected the performance of the cyclic de-icing heating system were ambient air temperature, heat distribution, and thermal lag."

Memorandum presenting an experimental investigation of various methods for the control of afterburner combustion screech at afterburner-inlet total pressures from 4000 to 6400 pounds per square foot absolute. Generally, the range of afterburner fuel-air ratios in which screech occurred and the intensity of screech did not vary appreciably in the range of pressures covered.

A method is presented for calculating the loading on a finite wing oscillating in subsonic or sonic flow. The method is applicable to any plan form and may be used for determining the loading on deformed wings. The procedure is approximate and requires numerical integration over the wing surface.

A centerless-ground, 0.25-in.-diam. by 0.75-in.-long sapphire single crystal exposed to an integrated thermal neutron flux of 2 x 10 19 nvt at a temperature of 350 deg C (660 deg F) did not change its dimensions appreciably simple beam, with slightly less force than was required to break a similar unirradiated rod. In a darkened room the irradiated sapphire begins to thermoluminesce noticeably at 280 deg C (535 deg F) and most of the amber or brown coloration produced by the pile exposure is retained after annealing for 24 hr at the pile exposure temperature of 350 deg C (660 deg F). (auth)

The following remarks are intended primarily to assist in the orientation of the PRP reactor control development program in a direction consistent with the basic objectives of the program as a whole, and to discuss certain aspects of particular control systems which have a bearing on the capabilities of the reactor with respect to these objectives.

Report presenting wing buffeting data obtained from a flight loads investigation of two jet-propelled swept-wing airplanes to study the effects of Mach number and reduced frequency on the wing buffet loads. Consistent trends were noted between the flight testing and wind-tunnel testing that the results of this particular test were compared with. Results regarding variation with penetration and dynamic pressure, variation with Mach number and reduced frequency, and estimation of wing buffet loads are provided.

Report presenting a wind-tunnel investigation in which dynamic models that included elastic simulation to study the flight characteristics of a swept-wing bomber with parasite swept-wing fighters coupled at the wing tips. The configuration represents an efficient owing arrangement in which the operational range of fighters can be increased. Results regarding the bomber alone, fighter coupled wing tip to wing tip, and fighter coupled on boom are provided.

Memorandum presenting a wind-tunnel investigation in which dynamic models that included elastic simulation were used to study the flight characteristics of a swept-wing bomber with parasite swept-wing fighters coupled at the wing tips. The configuration is meant to represent an efficient towing arrangement whereby the operational range of fighters can be increased.

The design of the Purex Off-Gas Treatment Facility requires the use of new dissolver off-gas jets which will be installed in series with present jets in the Purex in-canyon "donut" jumpers. When the new jets are placed in operation, the motive air and steam supply services to the in-canyon jets will no longer be required and the in-canyon jets will become flow restrictions in the dissolver off-gas train. Calculated values of pressure drop across these "dead" jets at maximum off-gas rate varied from about 18 to 7 inches of water depending on whether the dead jets were considered as sharp-edged orefices or venturi meters without downstream pressure recovery. In the preparation of process specifications for hets for the new facility, accurate values for the pressure drcp introduced by the dead jets were required to avoid oversizing the new jets with resultant waster of motive jet fluid.

Report presenting an investigation in the transonic blowdown tunnel to obtain static longitudinal force and moment characteristics of two wings, one with an aspect ratio of 1.73 and 3-percent-thick delta wing and one with an aspect-ratio-1.73 4-percent-thick clipped delta wing mounted on a slender body. Results regarding lift characteristics, drag characteristics, and pitching-moment characteristics are provided.

A Mach number measured in the subsonic diffuser was used experimentally as the inlet control parameter of a bypass control system for an axisymmetric supersonic inlet operated in combination with a J34 turbo-jet engine at Mach numbers from 1.6 to 2.0. The control maintained the inlet in either critical or supercritical operation, and, when set for critical diffuser operation, the control recovered from disturbances that placed the inlet in both subcritical buzz and supercritical operation. A slotted-rake orifice gave a more representative value of subsonic diffuser Mach number than the single total-pressure probe used as a control input.

Report presenting a discussion of the use of an effective rotor-blade momentum thickness in describing rotor-blade loss characteristics. A derivation of the necessary equations is presented for obtaining momentum thickness for given overall turbine performance, stator performance, and rotor geometric quantities.