Author: National Aeronautics and Space Adm Nasa

Publisher:

Published: 2018-11-12

Total Pages: 120

ISBN-13: 9781731149169

An experimental study of generic high-speed civil transport was conducted in the NASA Langley 8-ft Transonic Pressure Tunnel. The data base was obtained for the purpose of assessing the accuracy of various levels of computational analysis. Two models differing only in wingtip geometry were tested with and without flow-through nacelles. The baseline model has a curved or crescent wingtip shape, while the second model has a more conventional straight wingtip shape. The study was conducted at Mach numbers from 0.30 to 1.19. Force data were obtained on both the straight wingtip model and the curved wingtip model. Only the curved wingtip model was instrumented for measuring pressures. Selected longitudinal, lateral, and directional data are presented for both models. Selected pressure distributions for the curved wingtip model are also presented. Belton, Pamela S. and Campbell, Richard L. Langley Research Center DATA BASES; MACH NUMBER; SUPERSONIC TRANSPORTS; WIND TUNNEL MODELS; WIND TUNNEL TESTS; WING TIPS; NACELLES; PRESSURE DISTRIBUTION; PRESSURE MEASUREMENT; TRANSONIC WIND TUNNELS...