Front: Text describes action on various war fronts: Tunisia, Command, Air offensive, Russia, Southwest Pacific, Aleutians. Large world map shows the United Nations, Axis and Axis occupied areas, countries with Axis relations broken, and neutral countries. Inset maps show military activities across the globe during the week; Battle of Tunisia. Photographs: American infantrymen advance towards Gabes; Army's M-12 155mm gun; Bristol Beaufighters enroute to Wau. Back:Don't [help the enemy by making military information easy to get].

Front: Text describes action on various war fronts: Tunisia, Command, Russia, Southwest Pacific, China, Air offensive. Special illustrated section describes clearing mine fields in Tunisia. Large world map is keyed to text and shows United Nations, Axis and Axis occupied areas, countries with Axis relations broken, and neutral countries. Inset maps: Tunisia. Photographs: Planes wait to be ferried by barge to land; Convoy of Allied ships steam toward an Arctic port; Army trucks yield to aircraft along a road in Tunisia. Back: Text entitled "You may be eligible for the Army Specialized Training Program" describes the minimum requirements for the Army training program.

Front: Text describes action on various war fronts: North Africa, Southwest Pacific, China-Burma, Plans, Aleutians, Russia Large world map is keyed to text and shows United Nations, Axis and Axis occupied areas, countries with Axis relations broken, and neutral countries. Inset maps: Shrinking battle lines in Tunisia; Crimea and surrounding region showing Nazi held territories. Photographs: Army-Navy expedition lands at Amchitka; Army gunner sets up AA defense at the westernmost U.S. air base in the Aleutians; Navy Seabees take shelter in foxholes; Allied soldiers line up for chow in almost knee-deep mud. Back: Text entitled "So he can fight!" describes the Women's Army Auxiliary Corps.

Front: Text describes action on various war fronts: Attu, Wake Island, Southwest Pacific, Russia, China-Burma, Air offensive. Large world map is keyed to text and shows United Nations Axis and Axis occupied areas, countries with Axis relations broken, and neutral countries. Additional maps: Mediterranean Sea; Areas held by Japan in the Kurile and Aleutian Islands. Inset map: Attu Island. Photographs: Mass production methods in the southwest Pacific mimic those of Detroit; Red Stars mark Soviet Air Force planes made in America; Nazis frisk Yugoslav peasants accused of guerilla activities Back: The not-so-soft underside [African victory].

Front: Text describes action on various war fronts: Aleutians, Western Europe, Mediterranean, Russia, Southwest Pacific. Map: Shows military activity in western Europe during the week of May 10 to May 27, 1943. Inset maps: Aleutians, Present fighting area in Attu. Photographs: Images of a Grumman "Wildcat" fighter plane taken from the escort carrier, U.S.S. Altamaha. Illustration: Advance on Attu. Back: You can crack that tank! Text and illustrations show how an infantryman can defend against an enemy tank.

A guide to improving pastures for the purpose of increasing production during wartime.

Equations are given for the elastic behavior of initially curved sheets in which the deflections are not small in comparison with the thickness, but at the same time small enough to justify the use of simplified formulas for curvature. These equations are solved for the case of a sheet with circular cylindrical shape simply supported along two edges parallel to the axis of the generating cylinder. Numerical results are given for three values of the curvature and for three ratios of buckle length to buckle width.

Report presenting measurements made of the pressures of the tail surfaces of the Republic Aviation Corporation P-47B airplane in the full-scale tunnel. Pressures were measured over the horizontal and vertical tail surfaces for several angles of attack and angles of yaw with numerous control-surface deflections to provide a check on the design loads. Results regarding the normal-force coefficients and predictions of forces on horizontal tail surfaces are provided.

Report discusses the results of shear testing in which the heads of Du Pont explosive countersunk rivets were allowed to protrude above the skin surface before expansion and the protruding portions were removed after expansion. As the height of the rivet head above the skin increases, the tightness of the rivet was found to increase. The report concludes that it may be desirable to investigating filling an entire shank with an explosive charge in order to permit greater tolerances in the drilled hole diameter and still have consistently tight rivets.

Report presenting formulas for propellers for the rate of change of side-force coefficient with angle of yaw and for the rate of change of pitching-moment coefficient with angle of yaw. Charts of side-force derivatives are given for two propellers of different plan forms.

"A method is developed for calculating the performance of a dual-rotating propeller from the section characteristics of the blade elements. The method is applied to an eight-blade dual-rotating propeller and the computed results are compared with low-speed wind-tunnel tests of the same propeller in both the tractor and pusher positions. The computations are found to agree within the experimental accuracy of the measurements" (p. 1).

Report presenting an investigation of the force characteristics of single hydrofoils in order to help with preliminary hydrofoil design.

Bulletin presenting some information on obtaining the maximum angular velocities to which aircraft are subjected in flight. Some of the maneuvers explored include pitching, rolling, yawing, or combinations of the motions, such as spinning.

Bulletin presenting a short investigation in the 19-foot pressure tunnel to determine the aerodynamic characteristics of a rectangular wing model constructed to NACA 0012 airfoil sections. Tests were run with the air in the tunnel at 2 different pressures: atmospheric and 35 pounds per square inch absolute.

Report discusses the results of two tests: "1) aerodynamic tests to determine the effect of the slipstream and thrust from the powered propellers on the lift and trimming-moment characteristics, and 2) hydrodynamic tests to determine the effect of the powered propellers on the range of stable locations of the center of gravity (from Introduction)." Large differences in the stable range between half-thrust and full-thrust conditions were observed. Three effects of power were also involved in the location of the stable range of the center of gravity.

Report presenting a detailed method for determining the jet-boundary corrections for reflection-plane models in rectangular wind tunnels. The principal effects of aerodynamic induction and boundary-induced curvature of the streamlines are considered. An example is included to illustrate the method.

Report presenting an investigation to develop an instrument for the determination of rain densities in this range in flight. The major requirements for the instrument are ease of operation, minimum weight and bulk, rapid response, and simplicity of installation.

"General relationships for the lead susceptibilities of paraffins, cycloparaffins, and olefins are presented. Methods are described by which the lead response may be estimated for these hydrocarbon classes, whether the lead response is indicated by octane number, critical compression ratio, or indicated mean effective pressure as limited by knock" (p. 1).

Report presents and discusses the improvements in hydrodynamic and aerodynamic performance of a seaplane with a retractable planing flap instead of a conventional main step. A type of flap that could be used is described and tested for hydrodynamic stability. Results regarding the trim limits of stability, limiting positions of the center of gravity, and skipping are provided.

Report presenting a series of tests made in the 15-foot free-spinning tunnel to study the spin characteristics of a model of a hypothetical canard airplane, which was designed to be about the same size and have the same general aerodynamic characteristics as a Boeing B-247 airplane. The model spun normally and had excellent recovery characteristics.

"The thrust produced by a variety of exhaust stacks and nozzles, and the effect of these stacks and nozzles on the power of a single-cylinder R-2800 engine were investigated over a wide range of engine speeds and manifold pressures in a series of tests in the Pratt & Whitney experimental test department. From the data obtained it is possible to estimate the optimum form of nozzles and the available thrust for airplanes fitted with R-2800 engines under sea-level conditions" (p. 1).

"Tests were made of riveted double-angle columns to determine the total rivet strength that is required to make these built-up columns develop the strength predicted by the standard column formulas. Results of the tests led to the conclusion that the required rivet strength may be calculated by the beam method of design" (p. 1).

From Summary: "The heat transfer in the laminar boundary layer of a heated plate in flow at high speed can be obtained by integration of the conventional differential equations of the boundary layer, so long as the material values can be regarded as constant. This premise is fairly well satisfied at speeds up to about twice the sonic speed and at not excessive temperature rise of the heated plate. The general solution of the equation includes Pohlhausen's specific cases of heat transfer to a plate at low speeds and of the plate thermometer. The solution shows that the heat transfer coefficient at high speed must be computed with the same equation as at low speed, when it is referred to the difference of the wall temperature of the heated plate in respect to its "natural temperature." Since this fact follows from the linear structure of the differential equation describing the temperature field, it is equally applicable to the heat transfer in the turbulent boundary layer."

Report presenting performance data on a Trane exhaust gas and air heat exchanger. Heat transfer rates were measured using specified exhaust gas rates and ventilating-air rates. The measured thermal outputs and static pressure drops are compared with predicted magnitudes.