| 摘要 |
An airfoil (11) includes a leading edge surface that includes a noncontinuous curvature distribution. A stagnation region (21) of the airfoil (11) includes a curvature larger than adjacent segments (23, 25) to reduce heat transfer into the airfoil (11). The reduced curvature in the stagnation region (21) is surrounded by the adjacent segments (23, 25) with larger curvatures to tailor the airfoil surface to provide a desired balance between heat transfer properties and aerodynamic performance. |
