| タイトル | Helicopter rotor and engine sizing for preliminary performance estimation |
| 著者（英） | Talbot, P. D.; Lee, H. C.; Bowles, J. V. |
| 著者所属（英） | NASA Ames Research Center |
| 発行日 | 1986-06-01 |
| 言語 | eng |
| 内容記述 | Methods are presented for estimating some of the more fundamental design variables of single-rotor helicopters (tip speed, blade area, disk loading, and installed power) based on design requirements (speed, weight, fuselage drag, and design hover ceiling). The well-known constraints of advancing-blade compressibility and retreating-blade stall are incorporated into the estimation process, based on an empirical interpretation of rotor performance data from large-scale wind-tunnel tests. Engine performance data are presented and correlated with a simple model usable for preliminary design. When approximate results are required quickly, these methods may be more convenient to use and provide more insight than large digital computer programs. |
| NASA分類 | AIRCRAFT DESIGN, TESTING AND PERFORMANCE |
| レポートNO | 86A42829
AIAA PAPER 86-1756 |
| 権利 | Copyright |
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