Turbulent separated flow over and downstream of a two-element airfoil |
| |
Authors: | D. Adair W. C. Horne |
| |
Affiliation: | (1) NASA Ames Research Center, 94035 Moffett Field, California, CA, USA;(2) Present address: BMT Fluid Mechanics LTD., Teddington, Middlesex, England |
| |
Abstract: | Flow characteristics in the vicinity of the flap of a single-slotted airfoil are presented and analysed. The flow remained attached over the model surfaces except in the vicinity of the flap trailing edge where a small region of boundary-layer separation extended over the aft 7% of flap chord. The airfoil configuration was tested at a Mach number of 0.09 and a chord Reynolds number of 1.8 × 106 in the NASA Ames Research Center 7- by 10-Foot Wind Tunnel. The flow was complicated by the presence of a strong, initially inviscid, jet, emanating from the slot between airfoil and flap, and a gradual merging of the main airfoil wake and flap suction-side boundary layer.Research Engineer, NRC Research AssociateAerospace Engineer |
| |
Keywords: | |
本文献已被 SpringerLink 等数据库收录! |
|