| タイトル | Effect of Sweep on Cavity Flow Fields at Subsonic and Transonic Speeds |
| 本文（外部サイト） | http://hdl.handle.net/2060/20120009443 |
| 著者（英） | Plentovich, Elizabeth B.; Wilcox, Floyd J.; Hemsch, Michael J.; Tracy, Maureen B. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 2012-05-01 |
| 言語 | eng |
| 内容記述 | An experimental investigation was conducted in the NASA Langley 7 x 10-Foot High Speed Tunnel (HST) to study the effect of leading- and trailing-edge sweep on cavity flow fields for a range of cavity length-to-height (l/h) ratios. The free-stream Mach number was varied from 0.2 to 0.8. The cavity had a depth of 0.5 inches, a width of 2.5 inches, and a maximum length of 12.0 inches. The leading- and trailing-edge sweep was adjusted using block inserts to achieve leading edge sweep angles of 65 deg, 55 deg, 45 deg, 35 deg, and 0 deg. The fore and aft cavity walls were always parallel. The aft wall of the cavity was remotely positioned to achieve a range of length-to-depth ratios. Fluctuating- and static-pressure data were obtained on the floor of the cavity. The fluctuating pressure data were used to determine whether or not resonance occurred in the cavity rather than to provide a characterization of the fluctuating pressure field. Qualitative surface flow visualization was obtained using a technique in which colored water was introduced into the model through static-pressure orifices. A complete tabulation of the mean static-pressure data for the swept leading edge cavities is included. |
| NASA分類 | Aerodynamics |
| レポートNO | NASA/TM-2012-217577
L-20047
NF1676L-13087 |
| 権利 | No Copyright |
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