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RESULTS of an extensive experimental program for the development of monocoque magnesium wing structures, which culminated in the design and testing of a full-size wing for the PV-1 airplane, are evaluated here. Additional tests are now in progress on a B-26 section to evaluate various combinations of chordwise and longitudinal stiffeners. Practically all current aircraft construction is of the semimonocoque type, the authors say, adding that simplified construction, rigidity of surface, and overall cost reduction led to comprehensive investigation of magnesium as particularly suitable for such uses. As aircraft speeds increase, they point out that more aerodynamic efficiency will be essential. Monocoque magnesium structures, they conclude, should provide the necessary characteristics and should be better suited to mass production. Note: Any opinions expressed herein are those of the authors and in no way reflect endorsement by the Navy Department.

THIS paper-relates to the recovery of energy from the exhaust gas of aircraft reciprocating engines by means of the exhaust jet, the steady-flow turbine, and the blowdown turbine. The performance of a reciprocating engine compounded with these energy-recovery devices is discussed in detail. The operating conditions for maximum performance are presented, and the effects of engine cooling and knock limit on these conditions are considered. A comparison is made of the overall weight of the engine plus fuel for the various exhaust energy-recovery systems at several operating conditions and durations.

This paper discusses the problems involved in the design and development of an ejector cooling system for the XR-10 Helicopter power plant. Basic design problems are reviewed. Test experience on exhaust stacks, nozzles, mixing chambers, diffusers, baffles, carburetors and engines are discussed in detail.