In a low-speed wind tunnel, measurements were taken of the velocity vector in the flow field behind the wing of a combat aircraft model. The wing was fitted with a leading-edge root extension (strake) and could have either a plain leading edge or a deployed slat outboard. Four flow investigations were made; at three angles of incidence with the plain leading edge and at one angle of incidence with the slat deployed. The distribution of the total head deficit, the streamwise component of vorticity, and a measure of the circulation distribution in the wake of the wing were computed.
Flow Measurements in the Wake of a Wing Fitted with a Leading-Edge Root Extension (Strake)
1979
40 pages
Report
Keine Angabe
Englisch
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