Influencers By Generating Vortices TRIZ Cases

Flow directors on airfoils redirect freestream air to form co-rotating vortices that diffuse the main tip vortex core.

Segmented composite protection layers join at butt joints with a strap to maintain electrical continuity while minimizing thickness buildup.

An active winglet uses controllable airflow modification devices to adjust control surfaces during flight.

Strategic vortex generators on rotor blades delay boundary layer separation, reducing noise by 7 dB and improving efficiency by 5.3%.

An actuated vortex generator pivots on an acute axis to retract flush with the wing, eliminating internal storage needs and reducing ice accretion.

Spigot mounting formation connects wing tip device to wing spar via three connectors, resolving thermal expansion stresses and static indeterminacy.

A hinged drooped leading edge device extends vortex generators into airflow to energize the boundary layer and delay flow separation.

Flow fence on wing surface delays airflow separation on winglet inboard surface, increasing lateral stability at high sideslip angles.

Movable strut flaps in a gas turbine diffuser reduce flow separation during partial load conditions, increasing static pressure recovery.

Dynamic wing extensions deploy controllable airflow devices to lower fuel consumption without adding permanent structural stress or weight to the aircraft wing.

A plasma actuation surface generates high-frequency body forces to destabilize and dissipate tip vortices along airfoil boundaries.

Asymmetrical tail boom profiles with vortex generators improve stability while strakes counteract reaction torque.

A three-stage Amphfoil watercraft transitions between boat, skim, and ground effect modes using hydrofoils and a hydro-wing hull.

Segmented leading and trailing airfoils reduce induced drag, improving lift-to-drag ratio by 36%.

Wing box adapter section accommodates variable dihedral angles to attach diverse wing tip devices, reducing structural load on the main spar.

Modular winglets and truss spar collect solar energy, resolving structural integrity issues in high aspect ratio wings.

Aircraft rotational joint uses a dual-use locking mechanism to secure wing tip devices in flight and ground configurations.

Segmented electrode pairs with alternating polarity reduce power supply size and prevent opposite airflow in plasma actuators.

A segmented seal assembly bridges the gap between an aircraft wing and its tip device to maintain a flush aerodynamic profile.

Wing-mounted reversible propellers provide thrust and braking, reducing takeoff distance while maintaining cruise efficiency.

A curved planar wingtip extends aft of the trailing edge while remaining substantially planar with the wing to reduce induced drag.

Segmented wing tip device with increasing sweep angles stabilizes flow behavior and prevents leading edge separation at high angles of attack.

A wing tip device moves along a carriage guide track to reduce span while maintaining structural integrity.

An accumulator in a movable wing tip device stores energy via inductive couplers, eliminating wiring wear across foldable joints.

Segmented inflatable boots with flexible vortex generators shed ice via elastic deformation, preventing premature stalls from flow separation.

Multi-angle sensor mast computes combined turbulence intensity ratios from forward, aft, and side sensors to prevent zero values during reverse or side flows.

Segmented fin-shaped vortex generators extend vorticity fields across the wing span to increase lift without increasing drag during cruising.

Offset cut lengths transform sliding contact into translational movement, eliminating seal wear at the wing tip device interface.

Upstream guide vanes turn incoming airflow to reduce propeller blade angle of attack, resolving efficiency losses from high loading constraints.

A submerged vortex generator reduces aerodynamic drag by generating vortices within a surface depression.

Adjustable Coanda deflectors redirect exhaust into ribbon shapes, preventing thermal impingement damage during vertical take-off and landing operations.

A tri-wing unmanned aerial vehicle frame distributes lift vectors to enhance horizontal flight stability and reduce power consumption.

A wing tip device paired with a modified movable flight control surface optimizes span loading on existing aircraft wings.

A locking hook and pin assembly uses a biasing device to preload the connection between a folding wing tip and fixed aircraft wing.

Rotatable wing-like element adjusts angle of incidence via passive torque control to reduce structural loads at the wing root.