Influencers By Generating Vortices TRIZ Cases

A wing tip pod with a convex outer surface controls the shock position in the wing tip region to extend natural laminar flow.

A morphing wingtip device adjusts its dihedral angle to optimize aerodynamic performance across different flight conditions.

Specific geometric ratios of paired triangular vortex generators reduce drag and increase lift by delaying boundary layer separation at high angles of attack.

Segmented winglet control surfaces resolve the absence of a vertical tailfin by generating differential yaw moments through independent deflection.

A tail sitter aircraft refueling system moves fuel between tanks and a hose and drogue apparatus for aerial or ground operations.

Roughness strip trips boundary layer to ensure consistent turbulent flow, reducing structural weight and design conservatism.

Aircraft wing spoilers use gaps to choke airflow, reducing hinge moment and actuation complexity.

A foldable wingtip pivots via a spanwise hinge to extend the wingspan during flight.

Segmented upper and lower winglets with a reverse curve and ventral fin reduce induced drag while lowering the bending moment on the airplane wing.

A nacelle air intake uses movable deflection members to guide reverse airflow and maintain aerodynamic profiles during thrust phases.

Telescopic adaptive wings reduce induced drag and fuel consumption by dynamically adjusting span and dihedral angles across flight conditions.

A boundary layer control device uses shape memory alloy to deploy automatically and increase fluid layer thickness.

A scythe wingtip device uses a trailing edge cutout to reduce wetted area and minimize non-induced drag components.

Fluidic muscle actuators deform resilient vortex generator flaps to reduce aerodynamic drag on vertical tail planes and rudders.

An asymmetrical fuselage generates sideward thrust from main rotor downwash to counteract torque without actuators.

Independent tip orientation disrupts recirculated dust vortices, clearing engine air intakes during low visibility landings.

Distributed stall triggers activate sequentially along the wing span to control local airflow separation, reducing drag and preventing sudden stalls.

A retractable leading edge notch generates a vortex to increase lift force, eliminating drag penalties during cruise flight.

High-porosity plates near cavity leading edges thicken shear layers and introduce fine-scale turbulence, disrupting large vortices that generate acoustic tones.

A vortilon attached to the wingtip lower surface generates upstream-facing vortices to energize the boundary layer.

A rotatable winglet adjusts its orientation relative to the wing element to manage aerodynamic forces across different flight phases.

A deployable shoulder wing extends the leading-edge vortex spanwise along a highly-swept wing, resolving low-speed control issues and improving maneuverability.

Profiled lifting members on engine pylons capture oblique airflow to generate propulsive force, reducing induced drag without adding active control complexity.

Heating and bending thermoplastic laminate panels to form strakes, reducing flow separation at high angles of attack.

Actuators alter airflow characteristics over vertical tails, reducing weight and drag while maintaining yaw control reliability.