Wing Shapes TRIZ Cases

Separated wing pairs, lift propellers, and tail rotors enable stable cruise-to-hover transition while reducing wing and propeller-wash interference.

Fixed forward-canted rotors form a synthetic wing that evens spanwise lift and thrust, enabling VTOL and stable forward flight without added control surfaces.

A co-flow jet channel uses internal pressurizers and ducts to combine thrust and lift generation while improving fluid flow management.

Pressurized ducts embedded in a wing create tangential co-flow jets that combine propulsion and lift without separate aircraft fluid systems.

A co-flow jet uses internal pressurizers and ducts to redirect fluid for both thrust and lift, reducing the need for separate aircraft flow systems.

A co-flow jet channel integrates pressurized injection and suction flow to generate thrust and lift in one aircraft fluid system.

Overmoulding a coating against a precision-finished mould forms smooth aircraft leading edge panels that extend laminar flow and cut drag.

Segmented partial airfoils pivot together or fold compactly, enabling stable transitions between airplane and rotorcraft flight modes.

A pylon-and-strut engine mount shifts loads off the wing, enabling longer span, smaller chord, and lower trim drag in transonic aircraft.

A stiffness-tuned load-carrying member and actuators adjust wing twist during flight to improve aerodynamic efficiency and reduce fuel burn.

Angled multi-section wing hinges let aircraft switch between compact ground handling and extended in-flight stability.

Relocating BWB landing gear aft of the rear spar and below upper propulsors cuts drag while preserving wing fuel volume and access.

Differential proprotor thrust and rotor-blown nonplanar wings enable precise hover and safer VTOL transition without cyclic pitch control.

Blade connecting members share loads between neighboring wind turbine blades, enabling thinner inboard sections with better aerodynamics.

A pylon-and-strut wing layout moves engine loads off the wing, enabling smaller chord, longer span, and better transonic lift and drag.

A composite D-truss wing uses sandwich shells, shear webs, and rib members to manage flight loads while limiting UAV wing weight.

Span-wise channels on upper and lower wing surfaces dissipate pressure build-up to prevent shockwaves, cutting drag and fuel loss.

An airfoil brace containing a tension-carrying strut reduces buckling-related jury-strut needs, drag, and weight on transonic aircraft.

Polynomial surface equations define a 10% thickness-to-chord airfoil that forms an attached oblique shockwave for supersonic flight.

Uniform-depth outboard wing sections create space for joints and actuators, improving load transfer while supporting movable wing tip devices.

Undulating bionic airfoil surfaces generate vortex flow to limit low-speed stalling.

This case shows how an airfoil landing gear strut generates lift while preserving ground clearance and reducing storage needs.

CFD-optimized upper and lower surfaces generate attached oblique shockwaves, improving lift-to-drag ratios for supersonic aircraft.

A perforated panel skin with a micro-lattice stiffener structure enables airflow through the surface to maintain laminar flow over an aerodynamic body.

Turbulence-generating members increase heat transfer coefficients to reduce required bleed air volume, lowering engine fuel consumption.

Pin-coupled fairing fittings reduce air resistance and noise by maintaining wing surface proximity.

A variable camber leading edge adjusts its position to generate oblique shock waves near the airfoil front.

Movable suspension points shift the center of gravity on powered parachutes to maintain platform balance during flight operations.

Optimized pressure distribution near the leading edge reduces cross-flow instability, lowering friction drag while maintaining structural strength.

Segmented wing sections with nested propulsion units resolve mechanical strength and safety contradictions by protecting occupants from rotor hazards.

Thinned portions on the wing and strut expand the airflow channel to minimize shockwave strength and interference drag at transonic speeds.

Variable sweep geometry reduces compressibility drag at high speeds while maintaining stability and low skin friction drag.

Movable airfoil louvers dynamically adjust camber and thickness to resolve the contradiction between high lift at low speeds and low drag at high speeds.

Shock bumps stabilize wave position across flight conditions without variable camber complexity.

Internal L-profile connections eliminate external rivets that disrupt laminar flow, reducing fuel consumption and weight while enabling rapid component repair.

A stall-proof airfoil induces gaseous fluid flow across its lifting surface using pressurized gas injection to generate lift without wing movement.

A rotor assembly with a ball joint and tilt control changes the rotational plane of the hub to generate variable thrust.

A double wing aircraft design positions the gravity center within the front wing to generate positive lift from both surfaces.

A curved piccolo tube adapts to airfoil contours, resolving design constraints on slat layout and engine size while ensuring effective de-icing.

A hybrid unmanned aerial vehicle uses a balloon and electric engine to enable silent vertical take-off.

Vertical rotor pod separation reduces aerodynamic interference and noise while maintaining lift generation in eVTOL aircraft.

Riblet structures use thermal expansion elements to alter aerodynamic characteristics through shape changes.

Forward and aft wings with electric propellers resolve the contradiction between vertical takeoff capability and cargo volume.

Aerodynamic surface assembly directs fluid through curved passageways to create self-oscillating jets.