Aerodynamics of an Ogival Double Delta Wing: Control Authority With Split Elevons

作者：Daniel Sykes, Max P. Jones, Alex W. Mesny, Carl M. Sangan · 年份：2025 · DOI：10.2514/6.2025-0655 · 被引用次数：1 · 研究领域：Fluid Dynamics and Turbulent Flows、Aerodynamics and Fluid Dynamics Research、Aerospace and Aviation Technology

This paper presents the steady-state elevon (pitch) behavior of a sub-25 kg drone with an ogival double delta wing. The case study aircraft, "Kingfisher", is designed to be the first of its kind to exceed speeds of Mach 0.75. The delta wing planform minimizes wetted area for high-speed cruise whilst harnessing leading-edge vortices for low-speed, high-alpha maneuvers. Split elevons orient the aircraft in pitch and roll, and their sizing is crucial to its controllability. However, current analytical aerodynamic models fail to accurately capture the interactions between elevons and adjacent vortices. Moreover, the split elevon configuration employed here represents a gap in present experimental elevon studies. The study focuses on the low-speed control challenge during approach and landing, where the elevon-vortex interaction is critical. A 66% scale wind tunnel model was developed and tested in the University of Bath’s closed-loop wind tunnel. The model’s design combined additive manufacturing with a three-axis load cell to measure the lift, drag, and pitching moment at varying angles of attack and elevon deflections. The aircraft’s elevons exhibit linear changes in lift and pitching moment for deflections up to ±20°, beyond which stall occurs. The elevons are more resilient to stall at large angles of attack due to enhancement from the vortices. At these angles, the vortex cores are above the outboard elevons, and the inboard elevons are twice as effective as the outboard ele...