Abstract
The study presents results for experiments conducted in the transonic pressurized T2 wind tunnel of Centre d'Etudes et de Recherches de Toulouse. The 1/80th scale model of a modern subsonic transport aircraft was mounted in the test section using a fin-sting. It consisted of a fuselage, a detachable horizontal rear stabilizer, a belly fairing, and tip-truncated wings. The tip-truncated wings were designed by Aerospatiale to reproduce the correct downwash in the rear fuselage region. Tests were conducted at a freestream Mach number of 0.82 and a Reynolds number evaluated with the model chord length of approximately 2.5 x 10 6 . Various measurements were performed, mainly in the vicinity of the fuselage downstream rear part: oil-flow visualizations, pressure distributions, boundary-layer surveys along the fuselage symmetry lines and some lateral lines using a laser Doppler anemometry system, and near-wake surveys with both pressure and velocity measurements. These experiments were designed to allow a fine description of the flows developing along the rear part of a fuselage in a configuration similar to actual flight applications.
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
