Abstract: A blade of a turbomachine or a flying machine includes a blade airfoil extending in a radial direction from a blade root to a blade tip. The blade airfoil has an inflow-side leading edge, an outflow-side trailing edge, a pressure side and a suction side. A surface of each of the pressure side and the suction side extends between the inflow-side leading edge and the outflow-side trailing edge. The blade tip has an end face with a camber line that extends from the inflow-side leading edge to the outflow-side trailing edge. At least one tip-side recess forms a depression from the end face into the blade airfoil, the depression extending continuously from the pressure side to the suction side and having a partial length of the camber line.

Abstract: A blade of a turbomachine or a flying machine includes a blade airfoil extending in a radial direction from a blade root to a blade tip. The blade airfoil has an inflow-side leading edge, an outflow-side trailing edge, a pressure side and a suction side. A surface of each of the pressure side and the suction side extends between the inflow-side leading edge and the outflow-side trailing edge. The blade tip has an end face with a camber line that extends from the inflow-side leading edge to the outflow-side trailing edge. At least one tip-side recess forms a depression from the end face into the blade airfoil, the depression extending continuously from the pressure side to the suction side and having a partial length of the camber line.

Abstract: For the purpose of diminishing intake vortexes at jet engines with turbo-compressors of aircrafts, in particular during test runs, an apparatus is provided, which consists of a grating disposed near the ground below and directly in front of the engine inlet, which grating comprises short, approximately vertically extending wind tunnels.

Abstract: A projectile for shooting from a gun barrel in response to the force of a propellant gas emanating from the aperture of a propellant container, comprising a projectile body having a plurality of spin-producing propellant gas flow passages associated therewith, said passages annularly surrounding, and having their respective axes extending obliquely to, the longitudinal axis of the projectile body, wherein each passage has an inlet portion converging to an adjoining constricted portion, and a diverging portion extending downstream from the constricted portion, the axis of each passage being curved over the entire length of its converging inlet portion and substantially rectilinear over its diverging portion, and the walls of the diverging portion of each passage having a substantially rectilinear form, as viewed in the direction of propellant gas flow.

Abstract: In a projectile comprising a projectile body which is surrounded by separable guide means for said body in a barrel and/or has a separable propulsion member disposed between it and a propellant container, spin-producing passages adapted to be penetrated by propellant gas are provided in said guide means and/or said propulsion member.