Report presenting an investigation of the performance of several conical cooling-air ejectors at primary jet pressure ratios from 1 to 10, secondary shroud pressure ratios from 0.60 to 4.00, and primary to secondary temperature ratio of 1.0. The investigation centered on primary air flow, secondary air flow, primary nozzle thrust, and gross ejector thrust.

"The experimental performance of a modified turbine for driving a supersonic compressor is presented and compared with the performance of the original configuration to illustrate the effect of small changes in the ratio of nozzle-throat area to rotor-throat area. Performance is based on the performance of turbines designed to operate with both blade rows close to choking. On the basis of the results of this investigation, the ratio of areas is concluded to become especially critical in the design of turbines such as those designed to drive high-speed, high-specific weight-flow compressors where the turbine nozzles and rotor are both very close to choking" (p. 1).

Report presenting the results of an investigation of flap-type controls on a low-aspect-ratio triangular wing using NACA 0005-63 sections for a constant-chord and a constant-percent-chord control surface. Two flap profiles were investigated: one with a true contour and the other with a blunt trailing edge. Results regarding lift, drag, pitching moment, hinge moment, and rolling moments were obtained for several Mach numbers, a constant Reynolds number, and a range of angles of attack.

Report presenting effects of wing trailing-edge bluntness on aerodynamic characteristics of a wing-body combination at a range of Mach numbers and Reynolds numbers. Modifications were made to the rear half of a basic plane tapered wing of aspect ratio 3.1 and a 3-percent-thick, circular-arc, biconvex section with three types of trailing-edge shapes. Results regarding the lift characteristics, pitching-moment characteristics, drag characteristics, and maximum lift-drag ratio are provided.

A neutron burst from an untamped cylindrical Oy assembly occurred at the Pajarito Remote Control Laboratory at 1800 hours on 18 April 1952. The circumstances causing the burst and a description of the assembly involved are given There was no personnel hazard. Normal operations could have been resumed on other assemblies withing two or three hours after the burst. No evidence of damage to the oy was observed. It was determined that the burst resulted in 1.5 x 10(16) fissions in the oy. Also reported are some results of the computations and post-burst tests and a discussion of probable time behavior of power level during the burst.

Memorandum presenting an investigation to determine the increase in the useful ranges of flight conditions that may be obtained with a given jet-engine research facility when the choked nozzle technique or the exhaust jet diffuser, or both, are employed. The report describes the two methods, the considerations involved in their application, and typical results of their use as well as confirmation of the accuracy of data obtained by utilization of these techniques.