The 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.
Subsonic flow over thin oblique airfoils at zero lift
01.02.1976
Sonstige
Keine Angabe
Englisch
Subsonic Flow Over Thin Oblique Airfoils at Zero Lift
NTIS | 1948
|Subsonic Flow over Thin Oblique Airfoils at Zero Lift
NTRS | 1947
|Subsonic flow over thin oblique airfoils at zero lift
NTRS | 1948
|Subsonic flow over thin oblique airfoils at zero lift
Engineering Index Backfile | 1947
|Subsonic flow over thin oblique airfoils at zero lift
Engineering Index Backfile | 1948
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