Front: Text describes action on various war fronts : North France, South France, Italy, Pacific, Eastern front. Maps: France, Oblique view of southern France looking north up the Rhone River Valley, the Balkans. Inset map: Paris. Photograph: Aerial view of one of the ports in southern Italy just before the landings on southern France. Back: Map of Celebes Netherlands Indies

Front: Text describes action on various war fronts : Eastern front, Italy, Southwest Pacific, Central Pacific, Burma, China, North France, South France. Maps show: Japanese and American controlled areas throughout the Mariana and Caroline Islands; military actions in Europe during the week; Japanese advancement into Burma and China; France. Back: [text and ill.] Crew, 147,142 men and women [making/using war planes].

Front: Text describes action on various war fronts : France, Eastern front, Philippines, Italy, China. Maps: Europe; Where American 3rd and 7th armies joined forces [France-Germany]; Central Asia: China attacks/Jap drives/B-29 target [markers on a map of China near Chungking]; [Advances in Italy and the Balkans]. Photographs: Sgt. Lewis F. Clancy talks over old times with Petit Victor in Oise, France; B-24 Liberators are hit and downed by Luftwaffe in Austria. Back: A chronological series of maps illustrate the conquest and liberation of France [1939-1944]. Includes photograph: French children salute and wave at soldiers in an armored tank.

Front: Text describes action on various war fronts: France, Pacific, Italy, China-Burma, Eastern front. Maps: North Burma; France; Western Pacific; Warsaw. Insets: Palau Islands; Morotai. Back:"Mindanao, Philippine Islands." Two different oblique views of the island. The large image shows it as seen from the southwest.

Describes Army procedures "for establishment, control, and termination of teletypewriter connections involving one more more manual switching centrals" as well as relaying sets of messages through reperforator centrals.

Describes the organization, training, and operations of the Chemical Decontamination Company.

"These instructions are published for the information and guidance of all personnel charged with the operation and maintenance of the McIntosh Electric Corporation Model No. 5018 of Sinusoidal Machine, Portable, for Galvanic, Faradic and Rapid Sinusoidal Currents, 110-Volt, 60-Cycle, Medical Department item No. 7132005 ... in the field. They contain information on the operation and maintenance of the equipment ...."

Report details the methods of determining the heat-transfer rate, pressure drop, and drag power of high-altitude radiators. Performance charts are provided for a wide range of design variables.

From Summary: "A unit oil system and oil-weighing device designed for laboratory engine tests to permit the remote measurement of oil-flow rate and oil consumption is described. The system regulates the oil pressure and temperature and is closed to make possible the accurate measurement of blow-by gas. The oil is weighed by a self-contained diaphragm and pilot-valve assembly, which uses compressed air as the transmitting medium. Several of those unit systems have given satisfactory service for more than a year."

"Flat sheet panels of aluminum alloy (all 17S-T except for two specimens of 24S-T) were tested under normal pressures with clamped edge supports in the structures laboratory of the Guggenheim Aeronautical Laboratory, California Institute of Technology. The thicknesses used ranged from 0.010 to 0.080 inch; the panel sizes ranged from 10 by 10 inches to 10 by 40 inches; and the pressure range was from 0 to 60-pounds-per-square-inch gage. Deflection patterns were measured and maximum tensile strains in the center of the panel were determined by electric strain gages" (p. 1).

Report presenting a convenient technical method to evaluate changes in the airfoil characteristics resulting from an extension of the chord at the trailing edge of a propeller blade section. The method determines the change in the angle of zero lift, the ideal angle of attack, and the difference in these angles as a function of the angle and length of the trailing-edge extension.

From Summary: "Tests on the B-34 fin-rudder-tab assembly were performed in the NACA 8-foot high-speed tunnel. Two cases of tab flutter were studied. It was shown conclusively that the frequency of the original or heavy tab was too low and caused coupling with one of the lower bending frequencies. A general conclusion was made that the tab frequency should be considerably higher than the lower modes of the fin-rudder assembly because there is generally a weaker coupling between the tab and the higher mode responses."

Report presenting 10 practical-construction models of sections of helicopter rotor blades tested in the NACA two-dimensional low-turbulence pressure tunnel at atmospheric pressure. Lift, drag, and pitching-moment characteristics of blades representing the present method of construction of the YR-4A helicopter were determined.

Report presenting two low-drag airfoils, the NACA 747A315 and the NACA 747A415, which are designed to have reduced pitching moments about the quarter-chord point and moderately high values of the design lift coefficient and are tested in the tow-dimensional low-turbulence pressure tunnel.

Report presenting a method for predicting from basic airplane characteristics the elevator deflection required to maintain optimum landing attitude. Charts for evaluating the components of the equation for elevator deflection and a comparison of computed and measured values for 15 airplanes are included. The computed deflection is considered the minimum value required to maintain landing attitude due to variations in piloting technique.

Report describing the behavior of the heat meter when it is used in thermal circuits which are under the influence of transient potentials. Three scenarios are considered: a heat meter suddenly placed on a hot surface, a heat meter mounted on the interior surface of the cabin wall of an uninsulated airplane climbing through air of decreasing temperature, and a heat meter mounted on the interior surface of the composite cabin wall of an airplane climbing through air of decreasing temperature.

Report presenting the effect of Reynolds number on the aerodynamic characteristics of a low-drag airfoil section tested under conditions of relatively high stream turbulence. The data are presented as curves of section angle of attack, section profile-drag coefficient, and section pitching-moment coefficient against section lift coefficient for various flap deflections.

Report presenting results of compression tests of six paper-base plastic panels with outward-acting normal pressure. All panels failed by separation of the skin, either from the rib or from the stiffeners. Results regarding the introduction of air pressure and types of failures encountered are provided.

Report presenting some principles for designing the optimum hull for a large long-range flying boat in order to suit the requirements of minimum drag, seaworthiness, and ability to take off and land at all operational gross weights. The principles include the use of moderate gross-load coefficients, ample forebody lengths, and deep steps and the close adherence of the form to that of a streamline body of revolution with a moderate fineness ratio.

"A technical method is given for calculating the axial interference velocity of a propeller. The method involves the use of certain weight functions P, Q, and F. Numerical values for the weight functions are given for two-blade, three-blade, and six-blade propellers" (p. 53).

Report presenting a description of a short method of estimating propeller efficiency for a given operating condition. The efficiency is determined for any design condition by evaluating separately from charts the induced losses and the profile-drag losses. The report covers single-rotating propellers of two, three, four, six, and eight blades and includes charts showing the rotational-energy loss for the given operating condition.

Report presenting a study to determine the effect of several methods of increasing the knock-limited power on critical cylinder temperatures. The knock-limited indicated horsepower and cylinder temperatures were determined for a Wright R-2600-8 cylinder under specified operating conditions. The most satisfactory method of increasing knock limited power was found to be internal cooling with water and the least satisfacotry was increasing the engine speed.

Report discusses the results of an investigation into the effectiveness of water injection into the combustion end zone of a spark-ignition engine cylinder for the suppression of knock. The injection angle was found to be very important for obtaining maximum results. The results of various angles and amounts of water were examined.

Report presenting simple curves by which the basic pressure-drop characteristics of unheated tubular radiators can be corrected to operating conditions in which the radiator is heated and in which the Mach number of the tube flow is of appreciable magnitude. The only data required for the use of the curves are the radiator dimensions, the rate of heat input, the pressure and temperature ahead of the radiator, and the rate of mass flow of air through the radiator.