NASA MS(1)-0317翼型的固定铰链式襟翼设计结构
By designing a fixed hinged flap structure for the NASA MS(1)-0317 airfoil, the flap deployment mechanism was simplified, the aerodynamic lift enhancement capability was improved, the problem of insufficient aerodynamic lift enhancement and complexity in existing flap designs was solved, the lift requirements of general aviation aircraft during takeoff and landing were met, and production and maintenance costs were reduced.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- HARBIN
- Filing Date
- 2023-12-15
- Publication Date
- 2026-07-17
AI Technical Summary
The existing flap design of the NASA MS(1)-0317 airfoil has insufficient aerodynamic lift enhancement capability and a complex deployment mechanism with a large weight, making it difficult to meet the comprehensive performance requirements of general aviation aircraft.
A fixed-hinge flap structure for the NASA MS(1)-0317 airfoil was designed. The flap relative chord length is 29%, the fixed hinge relative sag is 15%, the flap leading edge relative radius is 6%, the flap relative thickness is 22%, the flap cabin horizontal length in the airfoil chord direction is 12%, the maximum designed flap deflection is 25°, the flap slot width is 1.4% of the airfoil chord length, and the slot overlap is 4.5% of the airfoil chord length. This design simplifies the flap deployment mechanism and improves aerodynamic lift enhancement.
Without increasing weight and complexity, the aerodynamic lift capability of the flaps is improved, meeting the lift requirements of general aviation aircraft during takeoff and landing, while reducing production and maintenance costs.
Smart Images
Figure CN117485547B_ABST