Nonstationary pressure distributions and aerodynamic derivatives are presented for a NACA 64A006 airfoil with oscillating flap in Mach number range from 0.5 to 1.00. Values for the reduced frequency between 0 and 0.39 are included. The results supersede a part of the earlier results given in NLR report TR F253. (Author)
Results of Pressure Measurements on an Airfoil with Oscillating Flap in Two-Dimensional High Subsonic and Transonic Flow (Zero Incidence and Zero Mean Flap Position)
1973
43 pages
Report
No indication
English
High-Incidence Airfoil Aerodynamics Improvement by Leading-Edge Oscillating Flap
Online Contents | 1998
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