This technical report includes (1) World-wide Network (Maps). (2) Fallout of Sr90 at selected sites during August. (3) Comparison of Sr90 collection by gummed paper and pot on the roof of HASL during August. (4) Sr90 contamination of cow's milk in Metropolitan New York. (5) Sr90 content of the upper air during April, May and June. (6) Total activity measurement of the upper air after the Castle Test series. (7) Sr90 content of tap water at HASL before the Castle Test series. (8) Sr90 content of urine and fetal bone in the metropolitan New York area during August.

Free flight tests of 45-deg swept wings of 3.15 aspect ratio and 0.54 taper ratio to measure wing damping and possible transonic flutter.

Report presenting free-flight tests made on two pairs of wings of aspect ratio 3.15, taper ratio 0.54, and 45 degrees sweepback in the transonic speed range to measure wing damping and to investigate the possibility of flutter. Results regarding the flight test and analysis and discussion are provided.

Abstract: "This report is a brief description of the most recent developments in logarithmic amplifiers and period amplifiers at the Knolls Atomic Power Laboratory. The theory of operation and circuit design are discussed. The operational characteristics of the amplifiers are greatly improved over those of earlier models by the use of feedback circuits and compensating circuits."

From introduction: "This report covers the development of nondestructive techniques for measuring quantitatively: (1) thickness of electrodeposited-nickel diffusion barriers, and (2) thickness of aluminum cladding on flat-plate fuel elements."

"An experimental investigation has been conducted to determine the dynamic stability and control characteristics in hovering and transition flight of a 0.13-scale flying model of the Convair XFY-1 vertically rising airplane with the lower vertical tail removed. The purpose of the tests was to obtain a general indication of the behavior of a vertically rising airplane of the same general type as the XFY-1 but without a lower vertical tail in order to simplify power-off belly landings in an emergency. The model was flown satisfactorily in hovering flight and in the transition from hovering to normal unstalled forward flight (angle of attack approximately 30deg)" (p. 1).

Abstract: "Observations on the metabolism of chyle cholesterol in the rat show that exogenous cholesterol entering the systemic circulation in chyle exists in lipoproteins of low density (including chylomicrons) migrating with a high Sf rate (i.e.>400) in the ultracentrifuge. Following entry into the systemic circulation these molecules are rapidly removed from the plasma. This "clearing" of serum chyle cholesterol is a tissue phenomenon, the liver being the predominant site. Within the liver the chyle cholesterol esters are at least partially hydrolyzed; hydrolysis apparently does not occur in the plasma to any appreciable extent. After its entry into the liver exogenous cholesterol, if normally metabolized, presumably mixes with and becomes indistinguishable from cholesterol produced by endogenous synthesis."

Report presenting an investigation to determine the aerodynamic characteristics of a cruciform 70 degree delta-wing missile configuration with 70 degree delta canard control surfaces at M = 1.41 in the 4- by 4-foot supersonic pressure tunnel. Modifications to the configuration included variation of the body length and canard area and the substitution of a series of very small span wings for the cruciform delta wings and canard controls.

Report discussing an investigation to determine the effects of aeroelasticity on the rolling effectiveness of a model of a McDonnell F3H-1 airplane wing. The plane was found to be subject to aeroelastic losses that varied with Mach number and altitude.

Report presenting an investigation to determine the effects of aeroelasticity on the rolling effectiveness of an 8.06-percent-scale model of the McDonnell F3H-1 airplane wing. The investigation used rocket-propelled models in free flight over a range of Mach numbers. The results indicate that the airplane is subject to aeroelastic losses varying from about 7 percent at Mach number 0.5 to 46 percent at Mach number 0.90 at sea level.

Report discussing details of curium's chemical properties, including gamma radiation, solubility, and absorption. A procedure for separating curium from americium and the preparation of terbium tetrafluoride, which lead to its discovery, is also included.

Report presenting an investigation of wings of aspect ratios of 4, 3, and 2 with a plan-form taper ratio of 0.5 and a thickness taper ratio of 0.33 to determine their transonic longitudinal characteristics and effects of tapering thickness ratio. Results regarding the combined effects of aspect ratio and thickness ratio and effects of tapered thickness ratio are provided.

"An investigation at medium to high subsonic speeds has been conducted in the Langley low-turbulence pressure tunnel to determine the static stability and control characteristics and to measure the fin normal forces and moments for a model of a wingless fin-controlled missile. With the horizontal-fin deflection limited to a maximum of 6 degrees, longitudinally stable and trimmed flight could not be maintained beyond an angle of attack of 17 degrees for a Mach number of 0.88 and beyond 20 degrees for a Mach number of 0.50 for any center-of-gravity location without the use of some auxiliary stability or control device such as jet vanes" (p. 1).

From Introduction: "Reported herein are the over-all engine performance and the starting and windmilling characteristics. Data are presented in the form of performance maps at each flight condition to show the effects of altitude and flight Mach number on various engine-performance variables. The effect of engine deterioration with operating time on performance is also discussed."

Report presenting an investigation to determine the static characteristics of a two-blade NACA 10-(3)(062)-045 propeller. Experimental data were obtained for a blade-angle range from -5 degrees to 40 degrees measured at the 0.75 radial station and for tip Mach numbers up to 1.0.

Report presenting an investigation of the section and panel characteristics and loads obtained from pressure measurements over a 35 degree sweptback wing at level-flight lifts for a range of Mach numbers. Section pressure distributions were taken at the root, midspan, and tip stations of a Douglas D-558-II airplane.

Report presenting an investigation to determine the effects of six stabilizing fin plan forms and three body-nose configurations on the static stability of a 20 degree cone-cylinder body of revolution that had a fineness ratio of 8.65. The fin plan forms tested were swept untapered fins with 45 and 60 degrees sweep angles, trapezoidal fins, and delta fins. Results regarding the normal force coefficient, pitching moment coefficient, and center of pressure are provided.

Report presenting the aerodynamic design and design-point performance of a 16-inch impulse-type supersonic-compressor rotor component with turning to the axial direction, including an off-design and stage performance analysis. Results regarding rotor component performance, discussion of rotor performance, stage consideration for rotor performance, stage performance, and stator performance are provided.

Report presenting an investigation at subsonic and transonic speeds of the aerodynamic characteristics of a wing-body configuration designated as a swept biplane, which is composed of a sweptback and sweptforward wing joined at the tips. Results indicate that the plan form prevents the abrupt pitch-up normally encountered on monoplane swept wings. Results regarding subsonic tests, transonic tests, and some additional design considerations are provided.

Report presenting thrust-reversal performance of several basic target-type jet reflectors of various sizes and with various modifications obtained with unheated air over a range of exhaust-nozzle pressure ratios. Maximum, or near maximum, reversal for any deflector occurred at a spacing which was mechanically feasible and did not affect nozzle air flow.

From Summary: "An experimental investigation of a series of four convergent-divergent exhaust nozzles was conducted in the Lewis 8-by-6 foot supersonic wind tunnel at Mach numbers of 0.1, 0.6, 1.6, and 2.0 over a range of nozzle pressure ratios. The thrust characteristics of these nozzles were determined by a pressure-integration technique. From a thrust standpoint, a nozzle designed to give uniform parallel flow at the exit had no advantage over the simple geometric design with conical convergent and divergent sections."

Report presenting an investigation to determine the effect of spanwise variations in thickness ratio on the aerodynamic characteristics of wings at transonic speeds. Lift, drag, and pitching-moment data rare presented for 3 wings with different taper ratios. Testing occurred over a range of Mach and Reynolds numbers.

Abstract: "A fast, linear air-ionization chamber has been developed for integrating and monitoring external heavy-particle beams. It consists of a thin-windowed air chamber in which the beam ionization light is viewed by a photomultiplier whose output is fed directly to a standard electrometer."

Report presenting an investigation to determine the effect of several chord-extension configurations at low speed on a variable-sweep airplane model with a partially cambered wing. Testing occurred at a designated Reynolds number based on the mean aerodynamic chord of the wing at 50 degrees sweep for average test conditions. Results regarding the effect of chord extensions at 50 degrees, 60 degrees, and 20 degrees sweep, effect of chord extensions on lateral stability, and a comparison with different wing modifications are provided.