From Introduction: "The object of this report is to investigate the effects of after-burner lighting on the engine behavior and control-system requirements of a controlled turbojet engine. In this report, a simulation procedure for the afterburner is developed (based on ref. 3), this afterburner simulation is coordinated with previously developed nonafterburning-engine simulation procedures (ref. 4), and the compensated interacting control systems of references 1 and 2 are used. The results of an analog investigation of the the effects of an afterburner light on several controlled turbojet-engine configurations are reported and evaluated."

Memorandum presenting an investigation conducted in the 27- by 27-inch preflight jet of the release characteristics of a dynamically scaled AVCO booster vehicle, internally carried store model from a scale simulated bomb bay of the B-52 airplane at Mach numbers of 0.64 and 0.93. Simulated altitudes were -11,800 feet and 50,000 feet. Successful releases were obtained at all Mach numbers and simulated altitudes of the test.

Investigation of the performance of Inconel 739 (a nickel-base alloy of low critical-element content) buckets in a J33-9 engine showed that Inconel 739 had an engine life at least equivalent if not superior to S-816 buckets operated at 1500 degrees F. Inconel 739 buckets had a small scatter in life and exhibited lower total elongation than S-816. Bucket life was less than that predicted on; the basis of stress-rupture considerations alone. The failure mechanism was probably influenced by fatigue.

The information in this report is based on experience with a similar unit installed on experimental pule columns in the 321 Building. These installations were made to demonstrate the feasibility of the system. In one case, the installation on the 2A Prototype Column, the differential pressure cell (D/P cell) bottom interface control system was monitored by a capacitance-type instrument. The other installations were made on glass columns and were monitored visually.

Report discussing testing on two wing-fuselage models with 45 degree sweptback wings and various missile arrangements, one with pylons underneath the wing and one with the missiles semisubmerged in the sides of the fuselage. A comparison of the drag of both types of models was made.

Methods of the Radiation Monitoring Operation of the Chemical Processing Department.

This report addresses the continuous plutonium isolation contactor.

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The success attending the use of azaserine as a specific inhibitor of one atage in the metabolic pathway leading to the synthesis of inosinic acid in pigeon liver prompted us to use this antibiotic in a similar attack on purine synthesis in Scenedesmus. However, investigation of the products produced during photosynthesis by suspensions of these algae in the presence of azaserine showed that a more widespread interference with metabolism had occurred. The purpose of this communication is to describe the nature of these effects and to attempt to assess their importance in a general picture of the metabolic effects of azaserine.

Well-type scintillation counters have found use in many radiochemical laboratories. A gamma scintillation well counter has been used to measure the gamma activity of liquid samples in the 325 Building counting room for about a year. This well counter has been built and calibrated so that gamma activity measurements made with it can be easily compared with measurements made with the gamma scintillation counter (GSC). The well counter is electronically identical to the present GSC and differs only in the shape of the crystal used and the physical arrangement of the lead shield. The crystal contains a well which allows a tube containing the sample to be inserted in the crystal. The physical arrangement of the detector greatly simplifies the preparation of liquid samples for activity measurement. The 325 Building well counter and its application to chemical research and plant process analysis will be discussed in the following paragraphs. An operating procedure is also included.

Report presenting flight testing of two 7.5 degree boattail bodies of revolution with constant base annuli and varying jet static-pressure ratios and simulated turbojet exhaust rocket motors in order to determine the jet interference effects on total-drag and base-pressure coefficients over a range of Mach numbers. Results regarding the total drag and base-pressure and base-drag coefficients are provided.

Report presenting a supersonic wind-tunnel investigation of the origin and distribution of store interference in the 4- by 4-foot supersonic pressure tunnel at Mach number 1.61. The separate forces on a store, a fuselage, a swept wing, and a swept-wing-fuselage combination were measured. Results regarding drag, lift, pitching moment, side force, and yawing moment are provided.

Memorandum presenting a supersonic wind-tunnel investigation of the origin and distribution of store interference performed in the 4- by 4-foot supersonic pressure tunnel at Mach number 1.61 in which separate forces on a store, a fuselage, a swept wing, and a swept-wing-fuselage combination were measured. The report presents data on a configuration which simulated a heavy-bomber airplane with stores of several shapes and sizes.

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A series method of determining two-dimensional vortex paths is considered and applied to the computation of vortex positions behind a slender equal-span cruciform wing at any angle of bank as a function of the distance behind the trailing edge. Calculated paths are shown for four bank angles. For a bank angle of 45 degrees comparison is made with the results of a closed expression given in NACA-TN-2605. For other bank angles water-tank experiments provide qualitative comparison. Satisfactory agreement is found for a sufficient distance downstream to include most practical missile-tail positions. The interference forces on an equal-span cruciform wing are calculated for five angles of bank (including the trivial case of zero bank) from the vortex positions found by use of the series.

Report presenting an investigation of an airplane configuration model with a 45 degree swept wing of aspect ratio 4.0 and a taper ratio 0.3 with a low swept horizontal tail to determine its longitudinal stability. Longitudinal aerodynamic coefficients and stability derivatives are presented as functions of Mach number over the test range. The results are compared to wind tunnel and rocket model data and generally show good agreement.

Memorandum presenting a preliminary free-flight study of the drag and stability of a series of short-span missile configurations with 80, 85, and 90 degrees of fin leading-edge sweep. Increasing the fin sweep decreased the drag markedly.

Report presenting a preliminary study to determine the possibility of utilizing a wingless configuration as a guided missile. The results indicated that the maximum trimmed lift coefficient developed by the wingless missile was somewhat smaller than that of the winged missile at a Mach number of 2.4.

Report presenting an investigation in the high-speed tunnel using the transonic-bump method to determine the characteristics of a jet control consisting of numerous holes located at the 65-percent chord line of a 35 degree swept semispan wing with an NACA 65A006 airfoil section. Testing occurred over a range of Mach numbers, angles of attack, and ejection-pressure ratios. Results regarding rolling-moment coefficients and aerodynamic characteristics in pitch are provided.