Analyse de la Couche Limite a l'Intrados d'une Aile en Fleche et en Incidence (Analysis of the Boundary Layer of a Delta Wing in Incidence)

摘要

A 60 deg delta wing at 15 deg incidence is tested in a wind tunnel. The wing is an ONERA D 200 mm chord. The flow velocity is 30 m/s. The model is equipped with five arrays of pressure measuring points. A representation of the isobars shows lines parallel to the leading edge. Graphics showing the velocity profiles, transversal velocities, and turbulences are presented.