Abstract: Techniques for message data compression in a live simulation environment are described. A message is compiled at a computing entity in a live simulation environment. The computing entity then determines a position and an orientation of another entity that will received the message through an over-the-air network in the live simulation environment. The computing entity then determines a compression level for the message, based upon the position and orientation of the second entity, and flags the message with the compression level. To preserve the resources of the over-the-air network, such as network bandwidth, the computing entity compresses the message according to the compression level prior to sending the message to its destination in the live simulation environment.

Abstract: Techniques for message data compression in a live simulation environment are described. A message is compiled at a computing entity in a live simulation environment. The computing entity then determines a position and an orientation of another entity that will received the message through an over-the-air network in the live simulation environment. The computing entity then determines a compression level for the message, based upon the position and orientation of the second entity, and flags the message with the compression level. To preserve the resources of the over-the-air network, such as network bandwidth, the computing entity compresses the message according to the compression level prior to sending the message to its destination in the live simulation environment.

Abstract: An aerodynamic system providing an airfoil having a chord length, a leading edge, and a trailing edge. The airfoil further includes a first airfoil surface extending from the leading edge to the trailing edge, a second airfoil surface opposite the first airfoil surface, extending from the leading edge to the trailing edge, an injection opening in the first airfoil surface, and a recovery opening in the first airfoil surface located between the injection opening and the trailing edge. A pressurized fluid source is in fluid communication with the injection opening and a vacuum source is in fluid communication with the recovery opening. An exemplary use of the aerodynamic system of the present invention provides the ejection of a mass of fluid out of the injection opening along a surface of the airfoil and drawing a mass of fluid into the recovery opening.

Abstract: A high efficiency forward swept airplane propeller includes a constant leading edge forward swept angle from the root to the tip. The forward sweep is created by leaning the blade leading edge tangentially toward the rotating direction on the rotating plane. The leading edge projection on the axial-radial plane is a straight line with constant axial position from the blade root to the tip. Alternate embodiments of the projection of the leading edge on the tangential rotating plane include: a propeller blade with a leading edge shape that has a smaller forward sweep angle (including 0 degree) in the inner portion of the blade and a larger forward sweep angle in the outer portion; a propeller blade that has a negative leading edge aft ward sweep angle in the inner portion of the blade and a positive forward sweep angle in the outer portion.