Two circulation control cambered elliptic airfoil sections with a thickness-to-chord ratio of 0.15- and 1.0-percent circular arc camber were evaluated subsonically to determine their aerodynamic characteristics. The two models, designated NCCR 1510-7067N and NCCR 1510-7567S, have a common leading edge but different Coanda surfaces.
Two-Dimensional Subsonic Wind Tunnel Evaluation of Two Related Cambered 15-Percent Thick Circulation Control Airfoils
1977
68 pages
Report
Keine Angabe
Englisch
Aerodynamics , Aircraft , Aerodynamic control surfaces , Boundary layer control , Airfoils , Wind tunnel models , Leading edges , Coanda effect , Camber , Flow separation , Lift to drag ratio , High lift , Aerodynamic drag , Pitch(Motion) , Wind tunnel tests , Aerodynamic configurations , Aerodynamic slots
Tema Archiv | 1973
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