Influencers By Generating Vortices TRIZ Cases

Segmented propeller blade leading edges disrupt airflow to reduce acoustic emissions during aerial vehicle operation.

Strake generates vortices to enhance lift, reducing drag while maintaining stability.

A split winglet assembly with a ventral fin counters vortices to reduce drag.

A movable discontinuity acts as a vortex generator to re-energize the boundary layer on lifting surfaces.

A foldable wing tip device pivots via a spherical bearing to reduce span during ground operations.

Temperature-driven shape memory alloy actuation deploys a vortex generator flap only during take-off and landing to reduce cruise drag.

Wingtip rotor unit recovers vortex kinetic energy to power electrical compressors, reducing fuel burn and eliminating Ram Air Turbine maintenance costs.

Optical light guide transmits illumination across foldable wing joints, eliminating wiring wear and reducing maintenance frequency.

Laterally offset aerodynamic auxiliary surfaces generate controlled vortices to deflect airflow along the aircraft underside.

Multi-segment nacelle chines translate along the fore-aft axis to adjust vortex position and strength, resolving the lift versus drag trade-off.

Segmented connection spar with through holes enables rapid servicing by eliminating trailing edge access.

Pneumatic actuators deliver timed fluid bursts that accelerate vortex instability, reducing hazardous rolling moments for following aircraft.

Streamwise hinge lines reduce reaction moments on locking pins, allowing wingspan expansion for fuel efficiency while fitting airport codes.

A bistable spoiler transitions between flush and deployed states to reduce lift-induced strain on aircraft wings during gust events.

Segmented air deflectors with apertures and scalloped edges reduce sound emissions while maintaining load management on wind turbine blades.

Deformable flap members transition between states to modify airflow, reducing aerodynamic drag and fuel consumption from oversized vertical tail planes.

Dynamic wing tip rotor reconfiguration reduces aerodynamic drag during forward flight while maintaining vertical takeoff capability.

A deployable vortex generator apparatus energizes airflow over wing surfaces to stabilize transonic shockwaves.

Inclined triangular faces deflect debris while trapezoidal sidewalls resist pressure loads, preventing flow separation on airfoils.

Extending propulsion devices along the spanwise direction eliminates gaps that cause vortices, reducing induced drag and enhancing lift generation.

A foldable wing tip pivots to adjust the wingspan configuration.

Vortex generating devices under the junction fairing create attenuating vortices to counteract induced airflow structures that increase viscous drag.

A winglet flow fence delays airflow separation on the inboard surface to enhance lateral stability.

A swing wing tip assembly uses dual rotation elements to transfer structural loads between movable and fixed wing portions.

Angled slotted fins circulate airflow to generate stabilizing vertical lift, reducing induced drag and power wastage while extending flight range.

Piezoelectric vane sensors measure bending stresses to calculate air data, reducing sensor weight and volume for micro air vehicle operation.

A wing tip joint uses a linking member with two offset parallel hinge lines to rotate the tip while maintaining flexible skin curvature.

Contoured anhedral winglets convert harmful rotor downwash into upward lift, reducing wing download during hover.

Undulating trailing edges on a rotorcraft fairing reduce aerodynamic drag by modifying wake structure, avoiding flow separation and turbulence.

Thermally conductive blades bridge window panes to equalize thermal fields, reducing thermo-elastic distortion from severe aero-thermal heating.

A fairing assembly with Coanda surfaces and vortex generators organizes angled fluid flow exiting vehicle ducts.

An oblique cross-brace spar links front and rear spars in a wing tip device to distribute loads, reducing rib count and assembly thickness.

Internal support base and recessed head connect vortex generator to aircraft wall, eliminating projecting mount edges that disrupt airflow.

Pivotable propulsion units orient thrust lines parallel or perpendicular to the fuselage axis for vertical takeoff and landing operations.

A retractable vortex generator integrates with leading-edge and trailing-edge aerodynamic surfaces to produce vortices only when needed.