NATURAL LAMINAR FLOW DESIGN OF FUSELAGE NOSE FOR SMALL SUPERSONIC CIVIL TRANSPORT

摘要

A natural laminar flow fuselage nose was designed numerically at scale and with a Reynolds number corresponding to the small supersonic civil transport QSST aimed to reduce friction drag. The natural laminar flow effect was evaluated using the transition analysis for the parametric modified fuselage nose from the baseline shape. As a result, the transition front, which is predicted as the contour corresponding to N =14, moved 2 m further downstream from the nose tip for the cases based on Sears-Haack body. On the other hand, slight deformation was applied for the cases based on QSST, preventing the flow from the windward side to the leeward side. A decrease of large cross-flow velocity was observed along with the resultant delay of transition front.