A previous report gave calculations for the pressure distribution over thin oblique airfoils at supersonic speed. The present report extends the calculations to subsonic speeds. It is found that the flows again can be obtained by the superposition of elementary conical flow fields. In the case of the swept-back 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 swept-back wing at Mach=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
1948-01-01
Miscellaneous
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English
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
Engineering Index Backfile | 1947
|Subsonic flow over thin oblique airfoils at zero lift
TIBKAT | 1947
|Subsonic flow over thin oblique airfoils at zero lift
NTRS | 1976
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