Detailed measurements of flow fields associated with low-speed turbulent boundary layers were made for the 17% thick GA(W)-1 airfoil section at nominal angles of attack of 10 deg, 14 deg, and 18 deg, Reynolds number 2.2 x 10, and Mach number 0.13. The data include pressure and velocity surveys of the pre- and post-separated regions on the airfoil and the associated wake. The boundary layer characteristics including regions of separation on the airfoil are also presented.
Experimental studies of flow separation and stalling on a two-dimensional airfoil at low speeds
1975-07-01
Report
No indication
English
Studies of Flow Separation and Stalling on One- and Two-Element Airfoils at Low Speeds
SAE Technical Papers | 1977
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