Aerodynamic performance analysis of a little penguin wing and penguin‐inspired wing is numerically conducted at a chord‐based Reynolds number Re = 10 5 to assess its feasibility for use in microair vehicles (MAVs). The results strongly suggest that penguin‐inspired wing shape performs in a superior manner at higher angles of attack ( AOAs ) in comparison to the traditional National Advisory Committee for Aeronautics (NACA) profile, with the stall occurring at AOA = 19 ° and 15° for the penguin‐inspired wing and NACA wing, respectively. For the penguin‐inspired wing, the maximum lift coefficient is 0.89 at the stall angle, while the maximum lift‐to‐drag ratio is 3.9 at AOA = 12 ° . The flow separation point on the wing’s upper surface exhibits a linear progression toward the leading edge as AOA increases up to 19°. Between AOA = 19 ° and 25°, an abrupt forward shift of the separation point occurs. The separation point location, when measured from the leading edge, demonstrates a systematic delay along the spanwise direction from root to tip. This spanwise variation in separation characteristics persists across all tested AOA , suggesting a consistent three‐dimensional flow behavior over the wing surface.
Masud et al. (2025) studied this question.