Aerodynamic force tests conducted in vertical wind tunnel; increase of 41.5 per cent in max. lift; angle of attack for max. lift increased 13 deg.; max. increase of 30 deg. possible in highest stalling angle.
Aerodynamic characteristics of slotted clark Y wing as affected by auxiliary airfoil position
Nat. Advisory Committee Aeronautics -- Report
1931
16 pages
31 Figs.
Report
Englisch
© Metadata Copyright Elsevier B. V. All rights reserved.
Wind-tunnel tests of Clark Y wing with narrow auxiliary airfoil in different positions
Engineering Index Backfile | 1932
|Wing Airfoil Aerodynamic Characteristics in Non-Stationary Transonic Flow
British Library Conference Proceedings | 1995
|