Front: Text describes action on various war fronts including Midway, Western Europe, Russia, Egypt, Southwest Pacific, Mediterranean, China, and Jugoslavia. Large world map is keyed to text and illustrates time zones around the world. Includes two inset maps: "Rommel drives east for Suez"; Nazi-Russian battles near Kursk. Photographs: Saboteurs' weapons, Port of embarkation, Allied leaders in the Middle East [Major Gen. Russell L. Maxwell, General Sir Claude Auchinleck], Armoured observation car, U.S. Army troops in shadow of the pyramids; British mechanized unit salvages a disabled tank; Blocking Nazi tanks;"Production hits its stride". Back: Poster features photographs of British weapons.

Text describes action on various war fronts: China, Russia, Western Europe, Southwest Pacific, Convoys, Egypt, Aleutians. Large world map is keyed to text and illustrates time zones around the world. Includes inset maps: The sixth year of war in the China provinces; The Russian central front; Battleground of the Middle East. Photographs: British gliders; Lady drivers; The FBI walked in; Royal inspection; Southwest fighting bases

Front: Text describes action on various war fronts: Russia, North Africa, Vichy fleet, Atlantic, Madagascar, Jugoslavia, Burma, China. Large world map is keyed to text and illustrates time zones around the world. Includes inset maps: Battle of Midway, Battleground in North Africa, Russian Front. Photographs: U.S. carrier is hit; Somewhere in Australia; Night bloom; Desert daybreak; Taken from Rommel; All-Chinese gun crew; Seagoing tractor on test; Ride through hell. Back: Text and illustrations promote the WEFT (Wing, Engine, Fuselage, Tail) method of aircraft recognition.

Front: Text describes action on various war fronts: Southwest Pacific, China, Aleutians, Atlantic, North Africa, Western Europe, Russia. Large world map is keyed to text and illustrates time zones around the world. Includes inset maps: China front, Russian front. Includes seven photographs. Back: Photographs show a variety of tanks utilized by the British Army.

Describes the steps and equipment necessary for cotton ginning and for the prevention of seed mixing.

Describes the life cycle of the beanstalk weevil, its habits, and the damage it causes to plants in the Estancia Valley of New Mexico.

Describes the necessary steps for logging farm woodlands and transporting and preparing the wood to be sold.

Report discusses the results of an experimental investigation of two low-drag wing-nacelle units suitable for use with pusher propellers. The benefits of adding a nacelle to the wing are detailed.

Note presenting a study of the electrical charge structure of thunderstorms by the use of continuously synchronized records of the electrical-potential gradient at the surface of the earth under the influence of active storms.

Report presenting an analysis of the probable aerodynamic section characteristics of a plain flap with various arrangements of internal balance. The results of the calculations previously obtained were found to be in agreement with the experiment. Some possible applications of the data to balancing tabs are also provided.

Report presenting force-test measurements in two-dimensional flow made in the 4- by 6-foot vertical tunnel of the characteristics of an NACA 0015 airfoil with a balanced flap with a chord 30 percent of the airfoil chord and a flap-nose overhang 35 percent of the flap chord. Results regarding lift, hinge moment of flap, pitching moment, drag, and tab characteristics are provided.

Report presenting force tests in two-dimensional flow in the 4- by 6-foot vertical tunnel of the characteristics of an NACA 0015 airfoil with a balanced flap having a chord of 30 percent of the airfoil chord, a flap-nose overhang 50 percent of the flap chord, and a tab having a chord 20 percent of the flap chord. Results regarding the precision and presentation of data, lift, hinge moment of flap, pitching moments, drag, tab characteristics, and balancing effectiveness of various overhangs are provided.

"In connection with recent tests of a 1/4-scale model pursuit airplane in the NACA 8-foot high-speed tunnel, gun openings having low drag were developed for installation in the nose of the fuselage. The increase in the fuselage-drag coefficient for the final form of openings was 0.0132 at a Mach number of 0.69 and at an angle of attack of 0 degrees. The corresponding drag coefficient based on the wing area was about 0.0005. The critical speed of the airplane was not affected by the gun openings" (p. 1).

Report presenting information about airfoils in cascade, including the angle through which the air is turned and where the cascade losses are located.

Report presenting an investigation in the 7- by 10-foot wind tunnel to determine the aerodynamic section characteristics of several arrangements of an NACA full-span high-lift lateral-control combination. The combination consists of a full-span flap of airfoil profile that retracts ahead of a narrow-chord full-span aileron. Results regarding coefficients, precision, plain airfoil, determination of optimum aileron-flap arrangement, section aerodynamic characteristics, and lateral-control characteristics are provided.

Report presenting an investigation of the performance of a mixed-flow impeller and vaned diffuser unit with several modifications in a variable-component supercharger test rig. The investigation covered impeller tip speeds from 800 to 1200 feet per second over the range of air flows from wide-open throttle to incipient surge. The results showed the supercharger to have a peak efficiency of 0.77 and a peak pressure coefficient of 0.61 with the impeller frontal clearance at 0.035 inch.

Report presenting a preliminary investigation to determine the suitability of ejectors actuated by the exhaust of a radial air-cooled aircraft engine for providing engine cooling air at the ground condition. Various length and diameter ejectors were tested for varying engine power for nine ejectors actuated by the exhaust of individual cylinders and three ejectors actuated by the exhaust of groups of three cylinders.

Report presenting a theoretical analysis of the performance of propellers extending to high values. Charts are presented that facilitate the selection of the most efficient propellers over a wide range of operating conditions.

"Test of 10-foot diameter, four and six blade single-rotating and dual-rotating propellers were conducted in the NACA propeller-research tunnel. The propellers were mounted at the front end of a streamline body incorporating spinners to house the hub portions. The effect of a symmetrical wing mounted in the slipstream ranged from 20 degrees to 65 degrees setting corresponds to airplane speeds greater than 500 miles per hour. The results indicate that dual-rotating propellers were from 0 to 6 percent more efficient than single-rotating ones; but, when the propellers operated in the presence of a wing, the gain was reduced by about one-half" (p. 319).

Report discussing an analysis has been made by the NACA of the effects of heat and compressibility in the flow through the internal systems of aircraft along with equations and charts are developed whereby the flow characteristics at key stations in a typical internal system may be readily obtained.

Report presenting testing of cooling blowers for air-cooled engine installations and an exploration of the methods used in the blower design and operating characteristics of the blowers over a range of flight speeds and altitudes. The results indicate that the blowers operate as a more efficient type of propeller cuff and in many cases provide considerably more pressure boost than using a cuff.

Report presenting a technique of testing wind tunnel powered models developed as a result of experience gained in the investigation of the static longitudinal and lateral staiblity and control characteristics of several powered models in the 7- by 10-foot wind tunnel. A discussion of the conditions to be investigated, methods of presenting and interpreting the data, and a suggested operating technique are given.

Report presenting an analytical study of the influence of full-span slotted and Fowler flaps on the requirements for horizontal tail surfaces. The elevator deflection required to land at three-point attitude, elevator deflection required to stall the airplane at altitude, and permissible center-of-gravity range have been calculated for a fighter-type airplane.

Report presenting a study of the performance of bombers powered by one, two, four, and six 2000-horsepower engines supercharged to 25,000 feet. The performances are computed and are based on drag coefficients equal to the best obtained on modern airplanes and on weight estimates obtained from modern Army Air Forces airplanes. A chart is provided with the coordinates of power loading and wing loading noted so that all performances can be compared.