| タイトル | Investigation of upper-surface-blowing nacelle integration at cruise speeds utilizing powered engine simulators |
| 本文（外部サイト） | http://hdl.handle.net/2060/19760023113 |
| 著者（英） | Meleason, E. T.; Wells, O. D. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1976-01-01 |
| 言語 | eng |
| 内容記述 | Various overwing nacelle designs were investigated on a representative four engine short haul aircraft configuration during a combined analytical and experimental program. Design conditions were M sub o = 0.7 and C sub L = 0.4. All nacelles had D shaped nozzle exits and included a streamline contoured design, a low boattail angle reference configuration, and a high boattail angle powered lift design. Testing was done with the design four engine airplane configuration as well as with only inboard nacelles installed. Turbopowered engine simulators were used to provide realistic representation of nacelle flows. Performance trends are compared for the various nacelle designs. In addition, comparisons are presented between analytical and experimental pressure distributions and between flow through and powered simulator results. |
| NASA分類 | AIRCRAFT DESIGN, TESTING AND PERFORMANCE |
| レポートNO | 76N30201
NASA-TM-X-73447
E-8806 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/184833 |
