Tests on 3 NASA (National Aeronautics and Space Administration) 0012 Airfoil Models of Dfvlr in the Nal 0.3 Tunnel: An Assessment of 2-D Wall Interference

摘要

Tests were conducted on three NASA 0012 airfoil models. A range of Mach numbers from 0.6 to 0.9 and incidence of the model from 0 degrees to 7 degrees with both free and fixed transition on the airfoil model, was covered. Flow visualization studies were also carried out at a few Mach numbers and incidence. Interference corrections were computed from wall pressures measured along the slat on the top and bottom liners of the modified test section and the corrected data compared with those from other tunnels. An analysis of the data on the three models of chord lengths 100mm, 150mm and 200mm respectively, from the standpoint of interference due to tunnel walls, is presented.