GrabCAD 模型信息
UAV Wing Design · 模型 50347
This wing was engineered as part of a long-endurance UAV platform targeting a 50 kg total weight and cruise velocity of 30 m/s at 1,000 m altitude. The aerodynamic profile is based on the high-lift Selig S1223 airfoil, selected for its superior low-speed performance and proven use in UAV applications. The final wing spans approximately 2.86 m with a mean chord of ~0.28 m, yielding a total wing area of 0.8 m². Computational flow simulations at an 8° angle of attack demonstrated sufficient lift (~500 N) to sustain flight, with a lift coefficient of 1.24 and drag coefficient of 0.076, achieving a lift-to-drag ratio of ~8.2. These results confirm that the wing meets aerodynamic requirements for steady-level cruise. Structurally, the wing was modeled with a composite carbon fiber skin, internal CFRP spar, and lightweight ribs. Finite Element Analysis (FEA) validated the wing’s integrity under distributed aerodynamic loads, showing a maximum deflection of 50 mm and a Von Mises stress of 160 MPa—well within the material's limits with a safety factor of ~3.75. The design supports modular attachment via a spar socket and reinforced root rib-bulkhead interface. Overall, this wing is flight-capable, structurally sound, and optimized for endurance and stability in moderate subsonic conditions.
- 格式
- STEP / IGES、SOLIDWORKS、Rendering、Text file、Other
- 分类
- Aerospace、Aviation、Military
- 标签
- airplane wi、airplane、flow simulation、aerodynamic analysis、airfoil simulation、uav wing design、wing
- 数据更新
- 2026-10-06T00:55:51Z
