A low-speed experimental investigation detailing the design and evaluation of a self-contained circulation-control wing is presented. A moderate aspect-ratio wing (3.34) utilizing a low-Reynolds-number S8036 profile was tested at . The trailing-edge jet was produced using two internal impellers drawing air off the wing tips. The effect of trailing-edge bluntness was examined as was the jet’s quiescent characteristics. Achievable jet-momentum coefficients were low, limiting circulation control to the boundary-layer control regime. Force-balance testing indicated that the circulation-control system could achieve a moderate zero-lift angle-of-attack shift; however, the primary effect of the jet was flow control at high incidence, in which stall was delayed significantly. The blunt trailing edge (Coanda surface) caused a significant increase in the minimum drag coefficient, reducing both the range and endurance parameters.
Experimental Evaluation of a Self-Contained Circulation-Control Wing
Journal of Aircraft ; 50 , 3 ; 764-777
2013-04-08
14 pages
Article (Journal)
Electronic Resource
English
Experimental Evaluation of a Self-Contained Circulation-Control Wing
Online Contents | 2013
|Online Contents | 1994
Circulation control wing model study
AIAA | 1995
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