| タイトル | Comparative wind tunnel tests of NACA 23024 airfoils with several aileron and spoiler configurations |
| 本文（外部サイト） | http://hdl.handle.net/2060/19950021555 |
| 著者（英） | Wentz, W. H., Jr.; Snyder, M. H. |
| 著者所属（英） | Wichita State Univ. |
| 発行日 | 1995-05-01 |
| 言語 | eng |
| 内容記述 | This paper reviews research efforts at Wichita State University sponsored by NASA Lewis Research Center to design and evaluate aerodynamic braking devices which will be smaller and lighter than full-chord blade pitch control. Devices evaluated include a variety of aileron configurations, and spoilers located at both trailing edge and near the leading edge. The paper discusses analytical modeling, wind tunnel tests, and for some configurations, full-scale rotor tests. Current designs have not provided adequate control power at high angles of attack (low tip-speed-ratios). The reasons for these limitations are discussed. Analysis and wind tunnel test data indicate that several options are available to the designer to provide aerodynamic slowdown without full-chord pitch control. Three options are suggested; adding venting in front of the control surface hingeline, using spoilers located near the leading edge, and using a two-piece control combining downward deflection inboard with upward deflection outboard. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 95N27976 |
| 権利 | No Copyright |
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