Abstract: An exhaust plume cooling device for cooling an exhaust gas plume to reduce deleterious heat effects on impinged and surrounding surfaces. The device is supportable in a position downstream of an exhaust nozzle of an exhaust gas plume-producing engine and configured to periodically interrupt the flow of exhaust gases by injecting fluid into the exhaust plume zone.

Abstract: An apparatus for suppressing shock-induced separation of high speed airflow from a relatively low-energy boundary layer. The apparatus may include an actuator or array of actuators configured to alternately inhale and exhale fluid and positioned to alternately inhale fluid from and exhale fluid into a boundary layer of a fluid mass flowing along the wall. The actuator may be positioned to inhale fluid from a boundary layer separation bubble induced by a supersonic shock wave propagated in the fluid mass.

Abstract: An exhaust impingement cooling device for reducing heating effects of an exhaust plume on an impinged surface. An exhaust nozzle exit screen is positioned across an exhaust plume flow path, and includes a plurality of flowpath diverging apertures that spread at least a portion of an exhaust plume that is being emitted along the exhaust plume flow path from an exhaust plume source. Flow control jets are arrayed within the exhaust plume flow path in respective positions where their operation will augment the flow of exhaust plume gases through the screen, thereby increasing the momentum and mixing of the exhaust plume with cooler ambient air.

Abstract: An exhaust plume cooling device for cooling an exhaust gas plume to reduce deleterious heat effects on impinged and surrounding surfaces. The device is supportable in a position downstream of an exhaust nozzle of an exhaust gas plume-producing engine and configured to periodically interrupt the flow of exhaust gases by injecting fluid into the exhaust plume zone.

Abstract: An exhaust plume cooling device for cooling an exhaust gas plume to reduce deleterious heat effects on impinged and surrounding surfaces. The device is supportable in a position downstream of an exhaust nozzle of an exhaust gas plume-producing engine and configured to periodically interrupt the flow of exhaust gases.

Abstract: An exhaust plume cooling device for cooling an exhaust gas plume to reduce deleterious heat effects on impinged and surrounding surfaces. The device is supportable in a position downstream of an exhaust nozzle of an exhaust gas plume-producing engine and configured to periodically interrupt the flow of exhaust gases.

Abstract: An apparatus for suppressing shock-induced separation of high speed airflow from a relatively low-energy boundary layer. The apparatus may include an actuator or array of actuators configured to alternately inhale and exhale fluid and positioned to alternately inhale fluid from and exhale fluid into a boundary layer of a fluid mass flowing along the wall. The actuator may be positioned to inhale fluid from a boundary layer separation bubble induced by a supersonic shock wave propagated in the fluid mass.

Abstract: An exhaust impingement cooling device for reducing heating effects of an exhaust plume on an impinged surface. An exhaust nozzle exit screen is positioned across an exhaust plume flow path, and includes a plurality of flowpath diverging apertures that spread at least a portion of an exhaust plume that is being emitted along the exhaust plume flow path from an exhaust plume source. Flow control jets are arrayed within the exhaust plume flow path in respective positions where their operation will augment the flow of exhaust plume gases through the screen, thereby increasing the momentum and mixing of the exhaust plume with cooler ambient air.

Abstract: A tapered micro-plow, or a series of tapered micro-plows, are submerged in a boundary layer just upstream of a reflection point of an oblique shock. Each micro-plow develops a beneficial pair of vortices which redistribute high energy flow within the boundary layer such that flow separation is prevented or delayed. The beneficial vortex pairs rotate about an axis that is parallel to the flow of fluid, and together rotate such that they induce a velocity on one another which tends to hold them near the surface and delay vortex lift-off.

Abstract: A prismatic vortex generator for attenuating flow separation which occurs during supersonic flow of air over structure such as an aircraft airfoil, its fuselage, surfaces forming a part of a jet engine inlet, or similar surfaces subjected to supersonic airflow. A series of prismatic vortex generators are provided, each of which is configured to generate a vortex which attenuates flow separation and weight drag resulting from the supersonic airflow. Each prismatic vortex generator has a prismatic shape with a base, leading and trailing ends, and sidewalls that incline toward and join each other to form an apex. The leading end of each prismatic vortex generators is inclined away from the direction of flow.

Abstract: A tapered micro-plow, or a series of tapered micro-plows, are submerged in a boundary layer just upstream of a reflection point of an oblique shock. Each micro-plow develops a beneficial pair of vortices which redistribute high energy flow within the boundary layer such that flow separation is prevented or delayed. The beneficial vortex pairs rotate about an axis that is parallel to the flow of fluid, and together rotate such that they induce a velocity on one another which tends to hold them near the surface and delay vortex lift-off.

Abstract: A prismatic vortex generator for attenuating flow separation which occurs during supersonic flow of air over structure such as an aircraft airfoil, its fuselage, surfaces forming a part of a jet engine inlet, or similar surfaces subjected to supersonic airflow. A series of prismatic vortex generators are provided, each of which is configured to generate a vortex which attenuates flow separation and weight drag resulting from the supersonic airflow. Each prismatic vortex generator has a prismatic shape with a base, leading and trailing ends, and sidewalls that incline toward and join each other to form an apex. The leading end of each prismatic vortex generators is inclined away from the direction of flow.