Front: Text describes action on various war fronts: France, Eastern front, Italy, Air war, Southeast Asia, China, Saipan, Pacific, Southwest Pacific. Maps: Finland, North Burma, France, Eastern front. Back: Text and color illustrations explain the importance of teamwork, preparation, and support in combined or amphibious operations.

Front: Text describes action on various war fronts : France, Eastern front, Italy, Marianas, Southwest Pacific, Southeast Asia, China. Map insets: Bay of the Seine, southeastern Asia, central Italy, Poland-USSR border. Back: Map of the Po Valley, Italy.

Front: Text describes action on various war fronts : France, Italy, Eastern front, Pacific, China, Japan. Maps: American-controlled areas around Geelvink Bay; Military actions in the south Pacific Ocean; Guam ; Europe. Inset map: Dutch New Guinea Back: Map of Japan and adjacent regions includes glossary of Japanese geographic terms and suffixes..

Front: Text describes action on various war fronts. Maps display the Normandy front, the eastern front, and New Guinea. Back: "Saipan! within the inner defenses." Includes 9 photographs.

Front: Text describes action on various war fronts : Eastern front, France, Italy, Marianas, Southwest Pacific. Maps: northern Italy; Pacific Ocean; Guam, Rota, Tinian, Saipan. Photographs: flight deck of aircraft carrier, unloading of LST, German submarine pen, weapons left during Lt. Gen. Stilwell's retreat. Back: Map of Europe as viewed from the Soviet Union. Scale [ca. 1:7,000,000] 1 map : col. ; 77 x 116 cm.

"This manual is a guide to the tactical employment of tank destroyer units both self-propelled and towed." (Page 1.)

Bulletin presenting an investigation of the effects of various camouflage paints and painting procedures on the drag characteristics of a 60-inch-chord low-drag airfoil in the NACA two-dimensional low-turbulence pressure tunnel.

"A systematic account is given in part I of the use of dimensional analysis in constructing similarity conditions for models and structures. The analysis covers large deflections, buckling, plastic behavior, and materials with nonlinear stress-strain characteristics, as well as the simpler structural problems" (p. 1).

Report presenting a note in two parts regarding simplified truss stability criteria. The first part covers the development of simplified criteria for the stability of planar pin-jointed trusses against buckling in the plane of the truss. The second part constitutes a report on tests carried out to verify the validity of the criteria developed in part one.

"A decrease in shear strengths for increasing D/t ratios was shown in a previous investigation of protruding-head aluminum alloy rivets in double shear conducted at Aluminum Research Laboratories in 1942. Since single shear joints are more common than double shear joints, it was desirable to extend the investigation to single shear joints. This reports describes the results of this investigation of single shear joints and also includes the results of the previous investigation on double shear joints" (p. 1).

Report presenting a series of tests on the Brewster XSBA-1 airplane to determine the effects of various tail modifications. Some of the modifications include variations of the chord of the elevator and rudder while the span and total area of the surfaces are kept constant and variations of the total area of the vertical tail surface. Results regarding the longitudinal stability and control and lateral stability and control are provided.

Pressure distribution measurements were made over an airfoil with slotted Frise aileron up to 0.76 Mach at various angles of attack and aileron defections. Section characteristics were determined from these pressure data. Results indicated loss of aileron rolling power for deflections ranging from -12 Degrees to -19 Degrees.

Report presenting an investigation in the two-dimensional low-turbulence pressure tunnel of three different types of NACA airfoil sections equipped with split flaps with chords 20 percent of the airfoil chord. The main purpose was to determine the maximum-lift characteristics of these low-drag airfoil sections with split flaps.

A method of constructing fins of nearly optimum proportions has been developed by the NACA to the point where a cylinder has been manufactured and tested. Data were obtained on cylinder temperature for a wide range of inlet-manifold pressures, engine speeds, and cooling-pressure differences. The results indicate that an improvement of 40 percent in the outside-wall heat-transfer coefficient could be realized on the present NACA cylinder by providing a thermal bond equivalent to that of an integral fin-cylinder wall combination between the preformed fins and the cast cylinder wall" (p. 107).

"Theoretical investigations have shown that, because air is compressible, the pressure-drop requirements for cooling an air-cooled engine will be much greater at high altitudes and high speeds than at sea level and low speeds. Tests were conducted by the NACA to obtain some experimental confirmation of the effect of air compressibility on cooling and pressure loss of a baffled cylinder barrel and to evaluate various methods of analysis. The results reported in the present paper are regarded as preliminary to tests on single-cylinder and multicylinder engines. Tests were conducted over a wide range of air flows and density altitudes" (p. 1).

"The Ackeret iteration process is utilized to obtain higher approximations than that of Prandtl and Glauert for the flow of a compressible fluid past a circular arc profile. The procedure is to expand the velocity potential in a power series of the camber coefficient. The first two terms of the development correspond to the Prandtl-Glauert approximation and yield the well-known correction to the circulation about the profile" (p. 385).

Report presenting an analysis of the effect of cooling-air blowers on thrust power using an assumed airplane. Results indicated that when aviation-engine heat exchangers are used above their design altitude, blowers may be used to give additional available pressure and to increase jet thrust. Results regarding airplane speed, altitude, fin width, physical significance of the heat cycle, and thermodynamic efficiency are provided.

Report describes the installation of six-cylinder blocks from two in-line aircraft engines on CUE crankcases, which permits the separate operation of any cylinder as part of a single-cylinder test engine. Using multicylinder-engine blocks for single-cylinder tests is advantageous because there is greater availability of standard engine parts and there is less temperature gradient. Modifications of the crankcase, camshaft-drive mechanism, and operation of the cylinder are described.

From Introduction: "Certain alternations of a qualitative nature may be performed in spite of the fact that a pressure change cannot be prescribed. It is the purpose of this paper to indicate a method by which qualitative alternation may be performed. It will be noted that the present method of contour modification will serve the intended purpose of the inverse method."

"An analysis is developed that makes it possible to integrate von Kármán's boundary-layer momentum equation directly. For this purpose, the skin friction coefficient is expressed as a function of the Reynolds number based on the boundary-layer momentum thickness and the boundary-layer shape is assumed to be constant. The integrated equation permits the boundary-layer momentum thickness at the airfoil trailing edge to be rapidly determined for the estimation of airfoil profile-drag coefficients" (p .1).

The effects of jet-motor operation on the stability and control characteristics of two fighter-type airplanes as determined by wind-tunnel tests of 1/5-scale models are presented. It is shown that the action of the jets is to cause a small loss in stick-fixed stability which is predictable from known theories.

Report presenting an instrument for warning the pilot of the approach of the airplane to critical speed conditions. The device closes a contact that completes the electrical circuit of a suitable warning indicators when a predetermined limiting Mach number is approached. It can be used to operate any electrical apparatus through the use of suitable relays.

Report presenting investigations to determine the knock-limited performance of blends of 90 percent by volume AN-F-28, Amendment-2 fuel, and 10 percent by volume of the following fuels: tert-amyl alcohol, 2,6-dimethyl-1, 4-dioxane, methyl tert-butyl ether, methyl tert-butyl ketone, methyl isobutyl ketone, mesityl oxide, acetone, and diisopropyl ketone.

Report presenting the use of current methods that include interference and compressibility effects to estimate pressures over and near turrets located on a wing in regions of high interference velocities. The agreement between measured and estimated pressures indicated that present methods are adequate for predicting approximate critical speeds and for estimating loads at subcritical speeds with sufficient accuracy for design purposes.