Subsonic flow over thin oblique airfoils at zero liftThe pressure distribution over thin oblique airfoils at subsonic speeds is studied. It is found that the flows again can be obtained by the superposition of elementary conical flow fields. In the case of the sweptback wing the pressure distributions remain qualitatively similar at subsonic and supersonic speeds. Thus a distribution similar to the Ackeret type of distribution appears on the root sections of the sweptback wing at M = 0. The resulting positive pressure drag on the root section is balanced by negative drags on outboard sections.
Document ID
19760011998
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Jones, R. T. (NASA Ames Research Center Moffett Field, CA, United States)