Abstract: A combination of an airfoil, turbine blade, or compressor blade with a flow separation control device includes an airfoil and a flow separation control device. The airfoil includes a body with an upper surface and a lower surface that extend from a leading edge to a trailing edge. The flow separation control device includes a plurality of openings on the upper surface of the body.

Abstract: A dual-wing aircraft includes a body extending from a front end to a rear end; a front wing, having: a first section secured to the body; and a second section secured to an opposing side of the body; a rear wing, having: a third section secured to the body; and a fourth section secured to the opposing side of the body; a tail wing rigidly attached to the body and positioned between the front wing and the rear wing.

Abstract: A method to control flow separation over an airfoil, turbine blade or compressor blade includes providing an airfoil having a body with an upper surface and a lower surface that extend from a leading edge to a trailing edge; providing a flow separation control device having a plurality of openings on the upper surface of the body and a plurality of capillary tubes in gaseous communication with the plurality of openings; and injecting gas through the plurality of capillary tubes into a portion of the airstream passing over the uppers surface of the body.

Abstract: A combination of an airfoil, turbine blade, or compressor blade with a flow separation control device includes an airfoil, a flow separation control device, and an injection system. The airfoil includes a body with an upper surface and a lower surface that extend from a leading edge to a trailing edge. The flow separation control device includes a plurality of openings on the upper surface of the body. The injection system includes an inlet tube, a pump in gaseous communication with the inlet tube, and a flow regulator in gaseous communication with the pump and the plurality of capillary tube.

Abstract: A system includes an elongated cylindrical body having a first end extending to a second end; an outer surface and an inner surface; a thickness extending from the inner surface to the outer surface; and a plurality of openings extending from the inner surface to the outer surface. The system further includes a fluid injection apparatus disposed within the elongated cylindrical body, the fluid injection apparatus is configured to pass fluid through the openings.

Abstract: A transonic aircraft includes a frame body extending from a fuselage to a rear tail wing section; an engine placed between the fuselage and rear tail wing section, the engine is secured to the frame body; a wing section includes a wing body with an upper surface and a lower surface that extend from a leading edge to a trailing edge, the wing body is oriented at an angle relative to an elongated length of the frame body; and a flow separation control device secured to the wing section. The flow separation control device includes a plurality of openings on the upper surface of the wing body.

Abstract: A hypersonic vehicle includes a body; a first engine secured to the body, the first engine is configured to create forward thrust at a first flight regime; a second engine secured to the body, the second engine is configured to create forward thrust at a second flight regime; and the hypersonic vehicle transitions between the first engine and the second engine during the first flight regime and the second flight regime.

Abstract: A rotary aircraft with a hybrid power source includes a streamlined body extending from a front end to a back end; a forward wing rigidly attached to and extending from a front section near the front end, the forward wing having a first section and a second section rigidly attached to the body and extending in directions opposing each other; an aft wing rigidly attached to and extending from a back section near the back end, the aft wing having a third section and a fourth section rigidly attached to the body and extending in directions opposing each other; a first rotor assembly secured to the first section and configured to create lift and thrust during flight; a second rotor assembly secured to the second section and configured to create lift and thrust during flight; a third rotor assembly secured to the third section and configured to create lift and thrust during flight; a fourth rotor assembly secured to the fourth section and configured to create lift and thrust during flight; and a center rotor assem

Abstract: A fuel detonation combustion pulse device includes a semispherical combustion chamber, a fuel supply system, a spark plug, a detonation accelerator, a hemispherical combustion chamber having a conic duct for transition to the detonation tube; a spark plug is mounted at the end wall of the sphere of the combustion chamber along its longitudinal axis, a fuel supply system is formed as a co-axial injector for fuel; an annular oxidant supply nozzle located perpendicular to the longitudinal axis of the device, and a detonation accelerator is shaped as a profiled stepped obstacle and is mounted in the combustion chamber conic duct for transition to the detonation tube being axial with it.

Abstract: A combination of a wind turbine blade with a flow separation control. The wind turbine blade includes a body with an upper surface and a lower surface that extend from a leading edge to a trailing edge. The flow separation control device includes a plurality of openings on the upper surface of the body.

Abstract: A method of creating a composite material with aggregate stability of carbon nanotubes includes carrying out submicron emission of Carbon Nanomaterial particles; conducting a dispersion analysis of the carbon nanomaterial particles of water suspension through a particle size laser diffraction analyzer; introducing carbon nanomaterial particles into a binder and mixing; adding resin into a mixture of carbon nanomaterial particles and the binder; applying a finished resin to a glass grid to create a saturated glass grid; drying the saturated glass grid, causing evaporation of binder volatile components; and slicing the glass grid into segments for analysis.

Abstract: A system to change a Mach number for different angles of attack with different speeds to achieving changing aerodynamic forces and velocity with a deceleration device integrated with a blunt body, the system includes a blunt body model having a deceleration device integrated into the blunt body model; a computational fluid dynamic module to perform data analysis on the blunt body model as the blunt body model receives fluid flow; a selection of Mach numbers to be inputted into the computational fluid dynamics module; a selection of angles of attack to be inputted into the computational fluid dynamics module; and contoured plots created via the computational fluid dynamics; the contoured plots relates to fluid flow around the blunt body model, with the contoured plots providing data relating to one or more of the selection of Mach numbers and one or more of the selection of angles of attack; and the contoured plots provides data analysis to be used to develop a design of a blunt body with optimal performance.

Abstract: A system for creating an analysis to be used in development of a design methodology for creating a blunt body with optimal performance, the system includes a first blunt body model lacking a deceleration device; a second blunt body model with a deceleration device integrated into the second blunt body model; a computational fluid dynamic module to perform data analysis on the first blunt body model and the second blunt body model; contoured plots relating to fluid flow around the first blunt body and the second blunt body as determined by the computational fluid dynamics module; the contoured plots provide a numerical analysis to be used to develop a design of the blunt body with optimal performance.

Abstract: A system includes an elongated cylindrical body having a first end extending to a second end; an outer surface and an inner surface; a thickness extending from the inner surface to the outer surface; and a plurality of openings extending from the inner surface to the outer surface. The system further includes a fluid injection apparatus disposed within the elongated cylindrical body, the fluid injection apparatus is configured to pass fluid through the openings.