The results of an experimental pilot study on the location time, for a sequence of N specified positions on a panel, are given for 1 <_ N <_ 30. The positions to be located were randomly arranged on one set of panels and arranged according to an ordering scheme on a second set of panels. Th location time for N positions randomly arranged on a panel varies approximately as N(2). In the case of an order arrangement the location time is essentially proportional to N. Even for as few as 30 positions, the location time for an random arrangement was twelve times greater than for an order panel. For 60 positions the ratio would be 19, and for 90 positions the ratio would be 26.

This report summarizes the effect of irradiation on the properties of fissionable and non-fissionable materials. General property changes, irradiation of zirconium, zirconium-tin alloys, the irradiation of aluminium, irradiation of thorium and uranium, are a few of the topics discussed.

A continuous belt drier capable of handling 1000 lbs of oxycarbonate per day was completed, installed, and operated to produce a satisfactory product for chlorination. An experimental chlorinator was also completed. All necessary pants were completed for the fabrication of Horizons' Mark VI continuous electrolytic cell. Evaluations of oxycarbonate materials for chlorination wiih varying chlorinating agents were made, and many of the variables such as water content and CO/sub 2/ values were established. Extremely ductile rods were obtained from the direct extrusion of Th metal powder. Plans were completed for the Mark VI electrolytic cell. Work was continued toward the development of a semi-continuous operating electrolytic cell of 7500-a rated capacity. (D.E.B.)

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Report presenting a wind-tunnel investigation to determine the effect of lowering the wing from the top of the fuselage to the bottom of the fuselage on the longitudinal characteristics of a wing-fuselage and a wing-fuselage-tail combination with the horizontal tail at various heights above the plane of the wing. The effects of wing height on the longitudinal characteristics of the model were small.

Report presenting an investigation to determine the effect of lowering the wing from the top of the fuselage to the bottom of the fuselage on the longitudinal characteristics of a wing-fuselage and wing-fuselage-tail combination with the horizontal tail at various heights above the plane of the wing. Testing occurred at a range of Mach and Reynolds numbers.

Report presenting an investigation of the low-speed static lateral stability characteristics of a complete model with a series of M- and W-wings. They were modified from a basic 45 degree swept wing and were designed to cover a range of spanwise locations of the sweep discontinuity.

Report presenting an investigation at low speed in the 300 mph tunnel to determine the static aerodynamic forces and moments on a missile model during simulated launching from 25-percent-semispan and wing-tip locations of a wing-fuselage combination. Results regarding the differences in location and effects induced by the fuselage are provided.

Report presenting a flight investigation at a range of altitudes to determine the wing loads on the Convair XF-92A airplane over the lift range of the airplane at subsonic and transonic speeds. Theoretical lift-curve slope for a delta wing was calculated and compared with the flight data at a Mach number of 0.75.

Memorandum presenting a low-speed wind-tunnel investigation conducted to study the effects of pylon-mounted wing tanks and speed brakes on the static stability characteristics of a model with sweptback wing and tail surfaces. The wing of the model was of aspect ratio 3.45 and was swept 40 degrees at the quarter-chord line. Results for the basic configuration and modifications to the basic configuration are provided.