Sea-level static testing of turbojet engine afterburner.

Report presenting a sea-level static investigation to determine the performance and some design principles for a short afterburner. The power section of a 12-stage axial-flow turbojet engine was used and the afterburner was designed to fit within the length required for the tail pipe used on the standard nonafterburning model.

From abstract: "A method for fabricating 30-in.-long stainless steel - uranium dioxide sheet was developed and the properties of the fabricated sheet were investigated."

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Results of preliminary tests with photographic emulsions using a lip target are discussed. Some methods for the search of heavy mesons are suggested. The preliminary tests with photographic emulsions were designed to investigate exposure conditions inside the Bevatron. These were carried out with stationary targets, since injected targets were not available at that time. The first exposure was designed to study the shielding required for emulsions placed in the direct beam (9 inches from the magnet conterline) during the entire acceleration cycle. Three 200{micro} Ilford G5 emulsions embedded in various thicknesses of brass were exposed for 30 pulses. Nominal maximum energy of beam was 3.5 Bev. During the second and third exposure (nominal maximum beam energies 4.1 and 6 Bev respectively) a lip target was placed in front of the emulsions. This was designed so as to dampen out the radial oscillations in the first section (.36 inches thick, 1/2 inch radial length). The beam should then hit the second section (.9 inches thick, .75 inch radial length) which is designed to reduce the beam orbit by {approx} 1 1/4 inches and then hit the emulsions on the next turn. 1/2 inch brass absorber was placed ahead of the emulsions.

Report presenting an investigation of an experimental 15-stage axial-flow compressor to determine the effect of inlet-annulus area blockage on disrupting the rotating stall and altering the overall performance and stall characteristics of the compressor. It is part of a general investigation to determine how to alleviate the general problems of blade vibration and poor off-design performance associated with compressor rotating stall.

Report presenting an investigation in the 8- by 6-foot supersonic wind tunnel to evaluate the performance of a translating-cone inlet operated over a range of Mach numbers and angles of attack. The effects of spike projection and internal flow area variation on pressure recovery, external drag, and corrected air-flow variation were determined.

A study of a series of three single-passage nozzles, designed to turn the flow at different velocity levels but to identical outlet conditions, in order to determine whether secondary-flow accumulations of boundary-layer fluids within nozzles could be minimized by use of low-velocity turning. Results indicated that the type of turning with subsequent acceleration is highly effective in minimizing secondary-flow accumulations at the corner where the suction surface joins the end walls.