Wing Shapes TRIZ Cases

Spring tensioner maintains strut tautness, preventing droop under varying loads while minimizing weight and aerodynamic drag.

Intermediate slide portions in the rib structure enable chord length modification via wire winding, resolving drag from discontinuous surfaces.

Dynamic rotor tilt and variable speed operation resolve the trade-off between vertical takeoff capability and cruise fuel efficiency.

Distributed propulsion around a closed wing resolves crosswind yaw instability in helicopter mode while maintaining efficient forward flight.

Narrow keels intercept inboard shocks while tip fins trap outboard waves, enhancing the lift-to-drag ratio by capturing wasted shock energy.

Dynamic multi-functional flight control surfaces adjust distributed flaps in real-time to suppress aeroelastic deflections and minimize drag on flexible wings.

Fluctuating jets prevent stagnation in tight wedge-shaped spaces, resolving thermal management challenges while preserving aerodynamic performance.

Segmented stiffness and actuators adjust the bump shape to reduce drag and buffeting across varying flight conditions.

Spanwise flow disruptors generate specific frequency fluctuations to stabilize laminar boundary layer flow.

Ducted flapping wings reduce noise and safety hazards while maintaining efficiency for vertical take-off.

A UAV airfoil design uses constrained local surface angles to generate virtual camber, enhancing lift and reducing drag at low speeds.

An asymmetric aircraft configuration positions a boundary layer ingestion engine at the rear fuselage to enhance propulsive efficiency.

Pivoting outer wing sections fold flat against the central fuselage to enable compact storage and horizontal launch.

Counteracting pressures embed cored members between fiber plies, resolving manufacturing complexity for tapered aerodynamic shapes.

A monolithic composite skin integrates spar sections and graded surfaces to eliminate fasteners.

Segmented wing design reduces induced and profile drag by optimizing aspect ratio while maintaining structural resistance.

Tilting propellers on a rhombohedral wing structure enable vertical take-off and landing.

Outer wing sections pivot via aerodynamic forces to eliminate dedicated drive weight and reduce radar signature.

Variable airfoils adjust lift coefficients based on angle of attack and Reynolds number, resolving low-speed instability and high-speed sensitivity trade-offs.

A morphing airfoil system uses inflatable bladders to dynamically adjust chord length, angle, and thickness for real-time aerodynamic control.

Aircraft rotors spaced laterally from the fuselage guide air smoothly to the rear wing connection, suppressing lift reduction caused by flow interference.

Micro-perforated wing walls enable boundary layer suction via perforated tubes, eliminating separate recovery circuits to simplify integration.

A transonic airfoil with optimized leading-edge curvature reduces pressure drag by altering the local pressure coefficient distribution.

A quad-wing VTOL aircraft uses stacked propellers on inboard booms for vertical lift and a tail-mounted cruise propeller for forward thrust.

Segmented wing design with varying profiles reduces drag from ammunition loads, improving forward speed and hovering performance.

A composite stiffener uses a fibre shell surrounding a foam core with side-by-side battens.

Dual airfoils on a single wing boost lift coefficients and payload capacity, resolving the trade-off between structural simplicity and flight predictability.

Rotatable arms and a closeout mechanism alter airfoil geometry to resolve the trade-off between adaptability and structural complexity.

Chord-wise hollow members suction air through a perforated panel skin to reduce skin friction drag while maintaining structural stiffness.

Adhesive bonding eliminates fastener-induced drag disruptions while integrated anti-icing preserves boundary layer stability.

A compound rotorcraft features a polyhedral lower wing with kinked sections to enhance aerodynamic efficiency and lift generation.

An asymmetrical shock bump modifies transonic flow structures to induce lambda-like wave patterns.

A strut-braced wing system uses a staggered configuration to minimize aerodynamic interference between the wing and strut.

Segmented wingtips with anhedral and control surfaces reduce adverse yaw without compromising aerodynamic efficiency.

Convex-concave-convex junction fairing profile minimizes shock wave formation during transonic flight, cutting wave drag by up to 3%.

Segmented attachment components secure a leading edge skin panel, allowing predetermined spanwise movement to maintain laminar airflow and simplify replacement.

A wing leading edge slat incorporates upper and lower surface gaps connected to a suction system that removes air from the channels.

Convex and concave airfoil curves boost lift gradient to reduce tail dimensions and attitude bump during low-speed flight.

Segmented conduit zones and movable panels expel debris before it enters the propulsion channel, maintaining efficiency despite contamination risks.

Center body lowest point location creates suction zone to enhance pitch control without increasing drag or weight.

SC362XX airfoil reduces shock strength and delays wave formation, eliminating drag creep while maintaining hover figure of merit.

Segmented actuation mechanism extends through duct structure to pivot door for flow control.