The S-38, model 28 is a nine passenger Sesquiplane powered by two Pratt and Whitney Wasp 410 HP engines and is intended for routes where the ability to take off and land from both land and water is essential. A description of the weight, construction, power plant, fuel system, landing gear, hull and floats, dimensions, flight characteristics, blueprints, and photographs are provided.

The Widgeon Wapiti is a military aircraft suitable for a variety of roles. It is a normal tow-bay wire-braced biplane and can be powered by a variety of the Bristol Jupiter series engines.

It is proposed in this report to explain the Gloster Hele-Shaw Beacham variable pitch propeller. It is a variable pitch propeller, which has been theorized to greatly improve the performance of an airplane or airship. An explanation of the way the propeller works and some of the physics behind propeller operation are provided.

In the present article, several suggestions will be made for shortening the otherwise long take-off distance. For the numerical verification of the process, I will use a graphic method for determining the take-off distance of seaplanes.

This report describes the leading crankless engine types, which have appeared in recent years. These types include: the Mitchell crankless motor car engine and the German Michel engine.

This report presents a survey of the latest German giant airplane projects. A description of the physical form of the airplanes, their performance, and some possible applications are provided.

The purpose of the experiments was to determine the difference in the strength of steel tubes welded by different methods, as compared with one another and also with unwelded, unannealed tubes, including; moreover, a comparison of the results obtained by experienced and inexperienced welders.

"Experiments with a two-stroke-cycle, crank case scavenging engine. Effect of systematic variation of the height of the scavenge and exhaust ports on the scavenging, as determined by gas analysis. The best results were obtained under conditions differing from the usual ones" (p. 1).

We propose to make a study of the difficulties in using stressed coverings and their appropriate solutions. Fatigue and buckling are also discussed.

The Goldfinch is equipped with the Bristol Jupiter Mark Vii engine. It is the all metal version of the Gloster Gamecock used by the R.A.F. A description of the construction, components, flying qualities, characteristics, drawings, and photographs are provided.

The S.5 is equipped with Napier Lion racing engine, all duralumin floats and has a top speed in excess of 300 M.P.H. A description of its design, flight characteristics, and some photographs are provided.

Circular describing the Glouster IV, which is a biplane designed for high maximum speeds. A description of the components, design, controls, performance, drawings, and photographs are provided.

The Avro Avian has a lift capacity of 828 lbs (including pilot). It is equipped with the Mark II A.D.C. Cirrus engine. Details regarding the fuselage, cockpits, controls, landing gear, wings, engines, characteristics, drawings, and photographs are provided.

The Sidestrand I is a twin engine bomber that has gone into production for Royal Air Force Squadrons. It seats three, and can carry a load in excess of 3500 lbs.

Circular presenting a description of the Parnall Imp, which is a new British light airplane that lacks any wire bracing, has an all-wood construction, and has general weatherproof qualities. Results regarding wings, fuselage, landing gear, engine, cockpit, characteristics, drawings, and photographs are provided.

The Mowe is equipped with a 420 H.P. Jupiter engine and can be configured to carry up to 10 passengers. Details of the aircraft design, landing gear, wing, characteristics, drawings, and photographs are provided.

Part I of this paper covers the constructional design of metal flying-boat hulls and does not elaborate any further. Part II deals with the actual construction process of the hull.

This report presents a brief survey of the uses of sheet-metal coverings in conjunction with the inner structure. A method of construction is presented as well as a discussion on the strength of sheet metal.

This report examines the take-off conditions of airplanes equipped with tractive propellers, and particularly the more difficult take-off of airplanes heavily loaded per unit of wing area (wing loading) or per unit of engine power (power loading).

This report tries to give a comprehensive survey of the most important propeller problems such as the shape of propellers and the effect of atmospheric conditions on propeller performance.

From Introduction: "The increasing use of airplane wings equipped with ailerons and the importance of knowing the aerodynamic characteristics of tail units (empennages) provided with movable parts (rudders and elevators) impart some interest to the so-called "empirical profiles." For this purpose we thought best to employ the method proposed by Munk for the approximate theoretical study of thin, slightly curved profiles, assimilable, from an aerodynamic view-point, to their mean camber line."

The propeller cannot be considered alone, but the mutual interference between propeller and airplane must be considered. These difficulties are so great when the joint action of propeller and airplane is considered, that the aerodynamic laboratory at Gottingen originally abandoned the idea of applying the efficiency conception of the test results. These difficulties and the methods by which they are overcome are outlined in this report.

As a rule, the actual lift distribution at the wing tips shows deviations from the theoretical distribution, so that an approximate evaluation of the distribution may be regarded as satisfactory. After a few brief remarks on the fundamentals of the exact computation, the method will be so presented that the lift distribution for deflected ailerons may be determined for other values of the parameter p from the results already obtained. Coefficients will then be given in the form of diagrams and numerical tables, from which the desired forces and moments can be easily obtained by substitution in the given equations.

"In the present paper I shall not consider the problem of the best arrangement of airplane and propeller, but only a simple method for designing a propeller for a given arrangement of airplane parts. The inflow to the propeller and hence the efficiency of the propeller is affected most by the fuselage. The effect of the wings and of the other parts lying in the propeller slip stream is much less and is also more difficult to determine" (p. 1-2).