Abstract: A method of using a delta shaped blade as an aircraft propeller, helicopter or autogiro rotor, or wind turbine propeller is presented. The invention combines the delta blade system with the use of torsion bars to achieve desirable control of blade twist. The invention uses blade twist to control the air loading on the craft; hence better control of maneuvering is achieved. The invention also optionally includes adjustable blade roots such that the sweep and aspect ratio of the delta blade is controllably variable. Compared to traditional propeller blade configurations, the invention boasts improved performance and enhanced aeroelastic properties. The invention is a far more efficient system providing economic advantages, higher speeds, and more durable designs.

Abstract: An underwater structure for supporting an above-water structure having an underwater portion immersed for some period of time underneath a water line of a body of water is provided. The underwater structure includes, but is not limited to, a turbulence reducing member connected with the underwater portion.

Abstract: An improved propeller blade is presented. The improved blade has a slot near the tip. This improved blade outperforms and is more efficient than other modified and unmodified blade tip configurations.

Abstract: The invention is directed to an improved internal combustion engine, having a symmetric cylindrical arrangement and using a bevel gear train to join multiple crankshaft sections. It provides for a naturally smoother operation with less vibration than in-line engines. Better efficiency is expected with the engine than with comparable in-line engines. Manufacturing is expected to be simpler and gasket-sealing better than the in-line and V types of engines. Compactness will add to the engine's utility.

Abstract: Provided is an aerodynamic body having rhomboid wings and internal torsion bars which can be twisted to affect a change in the shape of a wing. Individual or multiple swings can slide relative to the fuselage body to affect a change in sweep angle and aspect ratio. Provided is a method of controlling the aerodynamic properties, in order to affect stability and maneuvering, of an aerodynamic body by warping the wings by twisting one or more torsion bars located internal to one or more wings. Additional control can be exercized by sliding one of more wings relative to the fuselage to change the sweep angle and aspect ratio.