Front: Text describes action on various fronts and is keyed to map. Photographs: Japanese soldiers, Japanese submarine, Suicide planes, Japanese war industry, aerial view of damage to Tokyo. Map: East Asia and Pacific. Inset maps: 5480 tons of bombs a day! Back: World map with shaded areas showing liberated areas since 7 Dec 1941, enemy held areas as of 8 May 1945; dotted lines show battlelines as of 7 Dec 1941, 1942, 1943, 1944 and 8 May 1945.

Front: Text describes action on Okinawa, in Foochow, Tokyo, Mindanao. Maps: Pacific action flares; Okinawa; Foochow; Tokyo; Mindanao. Relief shown by spot heights and hill shading. Back: Paper bullets. Text describes propaganda leaflets as part of psychological warfare. Illustrations and text detail German and Jap Safe-Conduct Surrender Pass instructions.

Front: Text describes action in portions of China, Japan, Okinawa and the Philippines. Keyed to map. Map shows Allied and Japanese held areas as of 5 June 1945 in portions of China, French Indo-China, Korea, Thailand, Japan, and the Phillippine Islands. Back: Ribbons representing decorations and awards : wear them correctly! Decorations and awards, and service ribbons are illustrated with detailed instructions and diagrams describing how to wear them correctly.

Front: Text describes Pacific action. Map: Pacific action. Inset maps: Yanks push north on Luzon; Allied troops in New Borneo landings; Japs fall back toward Fr. Indo-China border. Back: Save : don't help delay V-Day! Illustration of fist raised in V for Victory sign with text admonishing no waste of materials.

Provides "information concerning the organization, operation, and capabilities of the signal heavy construction battalion to signal and communication officers and enlisted men of these battalions, and to all other interested personnel."

Discusses variations in the fiscal reporting periods used by state and local governments. Contains tables describing the fiscal year endings of various types of governments in the United States.

"This technical manual discusses the principal causes of failures of roofs on Army Buildings, outlines methods of repairing and renovating roofs and flashings, and describes reroofing."

Report presenting a series of tests to determine the bearing yield and ultimate strengths of samples of 1/4- and 2-inch-thick plate of aluminum alloy 24S-T and to establish nominal ratios of bearing-to-tensile properties for the commercial range of plate thicknesses. Results regarding individual bearing testing, ratios of average bearing to tensile properties, and ratios of bearing yield strength to tensile yield strength are provided.

"Blunt-nose and elliptical-nose overhangs of 0.35 and 0.50 flap chord and a plain overhang on a flap having a chord of 0.20 airfoil chord have been tested in two-dimensional flow on an NACA 0009 airfoil. The results of the tests are presented as aerodynamic section characteristics for several flap deflections with the gap at the flap nose sealed or unsealed. Tests were made also to determine the effectiveness of a tab of 0.20 flap chord on the plain sealed flap and on a sealed flap having an elliptical overhang of 0.35 flap chord" (p. 1).

Report presenting an investigation of a full-scale horizontal tail surface to determine the elevator-fabric deflection at high speeds and the aerodynamic effects of the fabric deflection. Two fabric-covered elevators differing only in rib spacing and a solid wooden elevator were tested. Results regarding fabric deflection and aerodynamic characteristics are provided.

Report presenting results of a full-scale horizontal tail surface made to determine the effect of elevator-profile modifications and trailing-edge strips on the elevator hinge-moment characteristics for elevators having fixed plan plan form and constant balance. Results regarding the basic data with the metal elevator, effect of trailing-edge angle, effect of nose shape, and effects of trailing-edge strips are provided.

Report presenting an investigation to determine the effect of varying the carburetor throttle settings on the flow characteristics at the outlet of the supercharger inlet elbow. Air flow tests were made at several carburetor throttle settings ranging from open to closed. Results regarding distortion and turbulence are provided.

From Summary: "An analysis of the nose-inlet shapes developed in previous investigations to represent the optimum from the standpoint of critical speed has shown that marked similarity exists between the nondimensional profiles of inlets which have widely different proportions and critical speeds. With the nondimensional similarity of such profiles established, the large differences in the critical speeds of these nose inlets must be a function of their proportions. An investigation was undertaken in the Langley 8-foot high-speed tunnel to establish the effects of nose-inlet proportions on critical Mach number to develop a rational method for the design of high-critical-speed nose inlets to meet desired requirements."

Report discussing tests to determine the performance of an aircraft engine cylinder using nitrous oxide to provide additional supercharging. The test results of injecting it as a gas and calculated results of injecting it as a liquid are described.

Report presenting a concept of a simplified vortex system of a rotor wake in order to obtain a formula for the normal component of induced velocity along the fore-and-aft diameter of the rotor disk of a helicopter rotors.

Efficiency tests have been conducted on a single-stage impulse engine having an 11-inch pitch-line diameter wheel with inserted buckets and a fabricated nozzle diaphragm. The tests were made to determine the effect of inlet pressure, Inlet temperature, speed, and pressure ratio on the turbine efficiency. An analysis is presented that relates the effect of inlet pressure and temperature to the Reynolds number of the flow. The agreement between the analysis and the experimental data indicates that the changes in turbine efficiency with Inlet pressure and temperature may be principally a Reynolds number effect.

Report discussing the results of power-off wind tunnel tests of a twin-engine cargo airplane equipped with wheel skis. Stability characteristics are described for two flap positions and three ski positions. The effect of fairing the main skis in the retracted position on the drag coefficient is also described.

Report presenting flight tests with a P-47D airplane to determine the flow characteristics on a section of the upper surface of the wing. The behavior of the wool tufts used to measure these characteristics was determined from motion pictures. The results indicated that the flow remained smooth over the test panel until the critical Mach number was exceeded by 0.08 at lift coefficient 0.10 and by 0.05 at a lift coefficient of 0.50.

Two-dimensional data were obtained in Mach range of from 0.40 to 0.94 and Reynolds Number range of (3.4 - 4.2) X 10 Degrees. Results indicate that thickness ratio is dominating shape parameter at high Mach numbers and that aerodynamic advantages are attainable by using thinnest possible sections. Effects of jet boundaries, Reynolds Number, and Data presented are free from jet-boundary and humidity effects.

Report presenting the results of a theoretical and experimental investigation of wall interference for an airfoil spanning a closed-throat circular wind tunnel.

Report discusses graphs of constants meant to be used with a knowledge of maximum total head loss, static-pressure decrement, and integral of total-head loss across the wake of an airfoil to determine the section profile-drag coefficient. Computations of free-stream Mach numbers for certain assumed types of total-pressure distribution in the wake are provided to compare theoretical drag coefficients as determined by other equations based on the momentum method. While some disagreements are found, the more rapid technique is usable for wide variations in wake shapes for a Mach number range of 0.5 to 1.0.

"Typical thrust and torque coefficients and increments, due to the propeller, in the ratio of the dynamic pressure at the tail to the free-stream dynamic pressure are presented for 10 full-scale airplanes. Calculations indicate that an error of about 2 percent mean aerodynamic chord appears possible in determining the neutral point from wind-tunnel tests or a model in the gliding condition if the propeller is operated at zero thrust rather than at the values of thrust coefficient indicated by the flight tests" (p. 1).

Report presenting an investigation of the characteristics of partial-span spoilers located at 0.75 of the chord on an NACA 66-series tapered wing, especially at high speeds. The effect of small spoiler projections was found to increase with an increase in speed until the critical Mach number was exceeded.

Report comparing the drag of an airplane with a conventional body with that of an airplane carrying cargo in a detachable airfoil-shaped body. Information about the performance, longitudinal stability, and control characteristics of a lifting-body cargo airplane is also provided and compared with a conventional cargo airplane.