Front: Text describes action on various war fronts: Western Europe, Iceland, North Africa, Aleutians, New Guinea, Australia, Burma, Russia. Large world map is keyed to text and illustrates time zones around the world. Map inset shows the Russian front. Includes photographs: Jap welcomers; Over barbed wire; The Nazi 88; Converted merchantman; U.S. Army's troopship of the skies. Back: This is Aid to Russia. 10 photographs are accompanied by explanatory text.

Front: Text describes action on various war fronts: Tunisia, Command, Russia, Southwest Pacific, China, Air offensive. Special illustrated section describes clearing mine fields in Tunisia. Large world map is keyed to text and shows United Nations, Axis and Axis occupied areas, countries with Axis relations broken, and neutral countries. Inset maps: Tunisia. Photographs: Planes wait to be ferried by barge to land; Convoy of Allied ships steam toward an Arctic port; Army trucks yield to aircraft along a road in Tunisia. Back: Text entitled "You may be eligible for the Army Specialized Training Program" describes the minimum requirements for the Army training program.

Front: Text describes action on various war fronts: U.S.S.R., Southwest Pacific, Italy, Air offensive Maps: Central Italy, Rumania/Poland, New Britain Island./ Inset maps: Cassino region; Chieti region. Photographs: Delivering supplies to troops in Central Italy, Gen. Eisenhower with Sir Charles Poetal and Sir Arthur Tedder after the Tehran conference, Gen. Sir Bernard L. Montgomery, and Gen. Sir Alan Brooke inspect Nazi prisoners on the Italian front in New Zealand; Germans prepare to evacuate the Crimea, Landing craft are protected by B-25 medium bombers at Arawe. Back: Illustration and photographs show the many ways Army nurses serve.

Front: Text describes action on various war fronts: USSR, Air war, Central Pacific, Southwest Pacific, Italy, Submarines, Southeast Asia. Maps: Western Europe; Caroline Islands; Eastern front. Includes photographs: German wood box mine, New Zealand soldiers hold captured German soldiers, German-laid mines explode outside Cassino, the destruction of Cassino by Allied bombs. Back: Map of North Burma.

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 American advancement and control of Korean and Japanese cities after Japan's formal surrender on 1 Sept., United States time Map shows Japan and Korea. Photographs: Gen. MacArthur signs Japanese surrender terms on Battleship Missouri; Japanese foreign minister Shigemitsu signs at Tokyo Bay ceremony; Allied prisoners of war at Omori, Japan, hail their liberators. Back: Text and color illustrations show United States Marines' activities.

Front: Text describes photographs: U.S. destroyer Shaw -- Third Fleet Unit -- Nazis march in Vienna -- 35th Infantry Division troops in Polch, Poland -- Joachim von Ribbentrop -- Signatures on the United Nations Security Charter -- Nipponese who helped capture the headquarters of Chinese 29th Army at Tungchow -- Pfc. Cecil Cunningham, of St. Louis, MO in Tokyo -- Navy Secretary Frank Knox draws the second number in the Third Selective Service drawing -- Five Michigan men leave a separation center at Fort Sheridan, Ill. after discharge. Back: Map shows eastern portion of the United States with population statistics by state and per person income payments in 1940 and 1944.

"This manual provides instructions for training commissioned or enlisted personnel in the tactics and techniques of forward observation."

"An investigation has been made at large scale of the characteristics of highly swept wings. Data were obtained at several angles of sideslip on wings having angles of sweep of plus or minus 45 degrees, plus or minus 30 degrees, and 0 degrees. The airfoil sections of the wings varied from approximately NACA 0015 at the root to NACA 23009 at the tip. Each wing was investigated with flaps under flection, partial-span split flaps deflected 60 degrees, full-span split flaps defected 60 degrees and split-flap-type ailerons deflected plus or minus 15 degrees" (p. 1).

"Flight tests have been made with a P-51D airplane to determine the effect of chordwise vanes on the amplitude of tail buffeting. The tests made during abrupt pull-ups to the buffeting boundary included strain measurements on wing and tail and tuft studies over the wing. The results indicate that the vanes tested have no appreciable effect on the amplitude of tail buffeting" (p. 1).

Report presenting the application of simple sampling procedures to gust data obtained from P-61 thunderstorm flights in Orlando, Florida. The results demonstrated that the observed values of maximum effective gust velocities tend to be functions of the record distance of cloud survey.

Report presenting a study of the characteristics of a large-scale triangular wing to include the effects of section modifications. The wing in this report is the same as the one in the previous report but features various degrees of rounding of the wing leading edge and wing maximum thickness rather than having sharp edges. Results regarding the effects of airfoil section modifications, visible trailing vortices, and surveys in the extended chord plane are provided.

Report presenting airspeed and altitude data obtained from Lockheed Constellation airplanes flying between New York and San Francisco during May and June of 1946 in order to determine the probability of reaching or exceeding given values of airspeed and Mach number. Analysis indicated that the total probability of exceeding the placard "never extend" speed depends primarily on the probability of exceeding this speed in descent. The probability of exceeding the critical Mach number is very negligible.

From Introduction: "Experimental investigations (reference 1) have shown that in some cases the thrust can be more than doubled by means of tail-pipe burning. A comparison is made of a standard turbojet engine, whose thrust is augmented by tail-pipe burning, and a ram-jet engine. The performance characteristics for the ram-jet engine were computed entirely from theoretical considerations and on the assumption that the burner-inlet velocity was constant."

Report presenting the results of an experimental investigation to determine the downwash in the region of the trailing vortex behind a trapezoidal-wing tip in a supersonic stream. Results regarding the downwash at spanwise stations, downwash at chordwise stations, and wake survey are provided.

Report presenting an investigation of a model of a tailless airplane in a high speed tunnel at a range of Mach numbers. Results are compared to those obtained from a sting-mounted model tested in the same tunnel and a semispan model tested with the wing-flow method. Information regarding basic aerodynamic characteristics, spoiler controls, lift characteristics, drag characteristics, pitching moment at zero lift, and stability and control is provided.

Report presenting testing of the low-speed aerodynamic characteristics in yaw of a 42 degree sweptback wing of circular-arc airfoil sections in the pressure tunnel. The wing had an aspect ratio of 3.94, taper ratio of 0.625, and no dihedral or twist. Results regarding lateral-stability parameters of plain wing, effect of wing flaps on lateral-stability parameters, effect of fuselage on lateral-stability parameters, a comparison with the NACA 64(sub 1)-112 wing, characteristics in the extended yaw range, and airflow characteristics in the region of a vertical tail are provided.

Report presenting a low-speed investigation to determine the effectiveness of a conventional aileron and various spanwise spoiler arrangements on a 42 degree sweptback wing. The rolling-moment characteristics of the aileron and the spoilers, as well as the aileron hinge-moment, normal-force, and balance-chamber pressure characteristics were determined for a plain wing and a wing equipped with several high-lift and stall-control devices.

Memorandum presenting a bibliography of unclassified aircraft fire literature consisting of reports from a 20-year period ending January 1, 1949. The reports are separated into the following categories: aircraft fire accidents and statistics, combustibles, ignition sources, fire protection, fire prevention, fire resistance of materials, fire detecting, fire extinguishing, and passenger protection or rescue.

Report presenting an investigation of the surface pressures of the outer and inner surface of the bubble-type canopy in order to determine their load requirements. Testing was performed on a Grumman F8F-1 airplane. The forces on the canopy was found to be the highest when the airplane is operating at high speed with the canopy closed.

Heat-transfer data from supersonic wind-tunnel tests of a heated 20 degree cone are compared with theoretical results obtained by the method for determining the convective heat transfer in laminar boundary layers in a compressible fluid developed by Hantzche and Wendt and with the method presented in NACA TN No. 1300. The experimental data are also compared with the results obtained by Eber at the Kochel Laboratory in Germany and it is found that Eber's results correspond to those obtained with a turbulent boundary layer on the cone. The results provide a qualitative verification of the effect of heat transfer on laminar boundary-layer stability that has been predicted theoretically by Lees in NACA TN No. 1360.

Report discussing the aerodynamic effects of length-beam ratios 20 and 30 as compared to length-beam ratios from 6 to 15. There was slightly more longitudinal stability and slightly less directional stability than in the lower ratios and not much change in the minimum drag coefficient.

Memorandum presenting a discussion of inlets with a circular cross section and a central body designed for high Mach numbers. The optimum proportion between external and internal supersonic compression is discussed in relation to the external drag and the maximum pressure recovery. Results and analysis regarding the maximum pressure recovery as a function of the cowling position parameter, the effect of the cone angle parameter on the maximum pressure recovery obtained, the highest pressure recovery obtained as a function of the central-body-diameter parameter, the maximum pressure recovery as a function of Mach number, and optical observations of the flow phenomena about the inlets are provided.

Report presenting an investigation of the mechanism of interaction of compression shock with boundary layer. Shockless pressure distributions at supercritical Mach numbers were found to be accounted for by a marked thickening of the boundary layer for some distance ahead of a shock wave.