In a low-speed wind tunnel measurements have been 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 data from each of these tests have been analysed to give 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. (Author)
Flow Measurements in the Wake of a Wing Fitted with a Leading-Edge Root Extension (STRAKE)
1979
42 pages
Report
Keine Angabe
Englisch
Aircraft , Aerodynamics , Flow fields , Vortices , Swept wings , Military aircraft , Airplane models , Leading edges , Strakes , Subsonic flight , Slender bodies , Wind tunnel tests , Flow rate , Loads(Forces) , Static pressure , Measurement , Flow visualization , Outboard , Wake , Foreign technology , Angle of incidence
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