Front: Text describes action on various war fronts: Russia; North Africa; Mediterranean; Belgian Congo; Western Europe; Solomons; New Guinea; Iceland; China; Siberia. Large world map is keyed to text and illustrates time zones around the world. Inset maps show Battle areas in the Southwest Pacific; the Mediterranean arena. Includes photographs: Well-dressed commando; Pudding for a Panzer; Avro Lancaster bomber; Moving tanks up; Tanks train in the U.S. deserts. Back: Russian Armored Vehicles. Includes text descriptions of 8 tanks and 28 photographs.

Front: Text describes action on various war fronts: Russia, Madagascar, New Guinea, North Africa, China, Solomon Islands, Shipping, Galapagos Islands, Western Europe, Iceland. Large world map is keyed to text and illustrates time zones around the world. Inset maps show The push on Port Moresby; The Russian front. Includes photographs: The flag goes up, Marine bombers take off, Badly damged hangar, Inspecting a Flying Fortress at Malta, Memorial services for those killed during the Battle of Midway, Business end of Pom-Pom, Catafighter, U.S. Marines toughen up each other. Back: Maps Are Not True For All Purposes. 15 illustrations are accompanied by text describing some of the methods used to represent the world on a two-dimensional surface.

Front: Text describes action on various war fronts: Russia, Madagascar, Solomon Islands, New Guinea, Aleutians, Far Eastern waters, Midway, China, West Coast, Western Europe, Mediterranean. Large map is keyed to text and illustrates time zones around the world. Inset maps show: Madagascar; Russian front (southern sectors), Madagascar in Africa Includes photographs: Night falls in North Africa; Stinger [twin machine-gun]; It was "impossible" [Capt. Edward Ellsberg's sub salvage work]; Blimps hunt subs. Back: Somewhere in Alaska. 13 photographs are captioned. Text headlined: Alaska's Defenders Go Underground. Includes map labeled: Still Our Northern Frontier.

Front: Text describes action on various war fronts: North Africa, Russia, Madagascar, Solomons, New Guinea, China, Burma, Western Europe. Large world map is keyed to text and illustrates time zones around the world. Inset maps show the drive on Port Moresby, East China, South Russia. Includes photographs: "Jap midget starts new mission", Testing M4 tanks, Japanese target [Port Moresby air field], Russian front-- Kuban sector, Victory fleet. Back: Jungle Warfare. 18 photographs showing scenes of jungle warfare accompanied by text describing the challenges faced by soldiers in that environment.

Volume provides a summary of the progress of each agricultural experiment station. Also includes statistics and selected studies.

From Summary: "The results of 60 different tests on 2 aluminum alloy 17S-T plate girders are presented to show the influence of size and spacing of stiffeners upon the buckling characteristics of shear-resistant webs within the elastic range. It is demonstrated that stiffeners increase the stability of a web by retarding the formation subdivided panels. An empirical method of proportioning stiffeners is proposed which recognizes both of these stiffener functions, and comparisons are made with design procedures based upon theoretical considerations of the buckling problem. Also, some experimental data are provided to show the effect of stiffener size and spacing upon ultimate web strengths."

Report presenting a study of the landing characteristics of various airplanes with special attention paid to problems with landing gear design. The planes ranged from 1000 to 50,000 pounds and in span from 28 to 149 feet. Results regarding the observed landing conditions, including attitude, vertical velocity, pitching velocity, rolling velocity, lateral velocity (or side drift), and landing gear loads measured during the tests are provided.

"Fatigue-tests were conducted on six specimens made from 3/4-inch-diameter 17S-T rolled-and-drawn rod for the purpose of obtaining additional data on the fatigue life of the material at stresses up to the static strength. The specimens were tested in direct tension using a stress range from zero to a maximum in tension. A static testing machine was used to apply repeated loads in the case of the first three specimens; the other three specimens were tested in a direct tension-compression fatigue machine" (p. 1).

"The results of a theoretical and experimental investigation to determine the critical compression load for a universal testing machine are presented for specimens loaded through knife edges. The critical load for the testing machine is the load at which one of the loading heads becomes laterally instable in relation to the other. For very short specimens the critical load was found to be less than the rated capacity given by the manufacturer for the machine. A load-length diagram is proposed for defining the safe limits of the test region for the machine" (p. 1).

"A Wright GR-1820-G200 cylinder was tested over a wide range of fuel-air ratios at maximum permissible power output as limited by knock with three different degrees of valve cooling. The valves used were stock valves (solid inlet valve and hollow sodium-cooled exhaust valve), hollow valves with no coolant, and hollow valves with flowing water as a coolant. Curves showing the variation in maximum permissible values of inlet-air pressure, indicated mean effective pressure, cylinder charge, and indicated specific fuel consumption with change in fuel-air ratio and valve cooling are shown" (p. 1).

Report presenting force-test measurements in two-dimensional flow in the 4- by 6-foot vertical tunnel to determine the characteristics of an NACA 0015 airfoil equipped with a straight-contour plain flap with a chord 30 percent of the airfoil chord. Results regarding the lift, hinge moment of flap, pitching moment, and drag are provided.

Tests were conducted on hydrofoil assemblies approximating an arrangement for use under seaplanes or surface boats. A series of hydrofoils, each supported by two struts, was towed at various depths ranging from partial submersions to a depth of 5-chord lengths. At depths greater than 4 or 5 chords, the influence of the surface of the water is small; hydrofoils operating at low speed will have characteristics similar to those of airfoils of the same section.

Report presenting a theoretical study of the effects of aileron adverse yawing moment on lateral maneuverability at a high lift coefficient. The study included the effects of changes in effective dihedral angle, vertical-tail area, and tail length.

Bulletin presenting the results of bending tests on a monocoque box with the door on the compression side. The results indicate that the effectiveness of a stress-carrying door depends on the intended function of the door.

"Tests of a second representative bomber nacelle on a low-drag wing at a large value of the Reynolds number were made in the NACA two-dimensional low-turbulence pressure tunnel. Results show the drag and interference of the nacelle on the low-drag wing to be small" (p. 1).

Report presenting a brief, nontechnical discussion of condensation trails for flying personnel. World maps showing trail-forming zones at different altitudes and seasons are presented. Means for suppression trails are given.

Report presenting flight tests conducted to measure the lateral-control characteristics of an airplane, equipped with a lateral-control system, in which as the flaps are lowered the ailerons droop and a gradual transition of lateral control from ailerons to spoilers takes place. The variation of maximum rolling velocity with lateral stick movement as obtained in abrupt rudder-locked rolls was satisfactorily smooth except when control was by spoiler alone.

"Three widely different nose shapes were tested on a fuselage alone and on a complete model in the UACA stability tunnel to investigate the effect of cowling shape on stability characteristics. The results are presented in the form of charts which show the variation in the aerodynamic characteristics with the three nose shapes for the propeller-removed condition over a wide range of angles of attack and yaw. The results of the investigation indicated that large changes in the cowling shape produced relatively small changes in the aerodynamic characteristics" (p. 1).

Report presenting an investigation of the stalling characteristics of the Supermarine Spitfire, which was made as part of the flying-qualities measurement of the airplane. The results are presented in the form of time histories of the motions and controls during stalls in various conditions of flight. Generally, the Spitfire possessed good stall warning in the form of buffeting and stall motions were not violent.

Report presenting the flying qualities of the Supermarine Spitfire airplane. A variety of information regarding the construction, installation, longitudinal stability and control, and lateral stability and control are provided.

Report presenting ground-effect tests made in the LMAL 7- by 10-foot tunnel of a model of a low-wing, pursuit-type airplane equipped with a full-span 25-percent-chord slotted flap. Testing occurred at different heights and power conditions, and two stabilizer and elevator settings were used at each condition. Results indicated that the elevator deflection required for landing in a three-point attitude with the full-span slotted flap was considerably greater than that required with a partial-span split flap.

Bulletin presenting an examination of a part of the anti-icing equipment for a Ju 88 airplane, including exhaust-air heat exchangers, control valves, air duct system, and air-heated wing panels. Testing was performed on the components and indicated that the thermal ice-prevention equipment can maintain the outer-wing panel free from ice.

Report presenting an investigation to determine whether the use of a 78 degree countersinking tool instead of a 82 degree countersinking tool for riveting would substantially alter the conclusion reached in a previous paper regarding the placement of rivets for maximum strength.

Report presenting an analysis of experimental and theoretical data, which indicates that critical evaluation of fuel performance, especially economy, must be made in the engine. Data show that heating value is, from the aspect of fuel economy, not so important an aviation-fuel specification as believed. The knock ratings of fuels are affected by spark advance.