...
  • 主题
高级搜索  >
历史搜索 清空历史
首页> 外文期刊>Journal of the American Helicopter Society >Rotor Performance of a UH-60 Rotor System in the NASA Ames 80- by 120-Foot Wind Tunnel
【24h】

Rotor Performance of a UH-60 Rotor System in the NASA Ames 80- by 120-Foot Wind Tunnel

机译：NASA Ames 80 x 120英尺风洞中UH-60转子系统的转子性能

获取原文
获取原文并翻译 | 示例
           
页面导航
  • 摘要
  • 著录项
  • 相似文献
  • 相关主题

摘要

A full-scale four-bladed UH-60 rotor system was tested in the NASA Ames 80- by 120-Foot Wind Tunnel. A quality data set at low forward speed, 0 to 80 knots, has been obtained to support future rotor developments and analysis improvements. To evaluate the NASA Ames 80- by 120-Foot Wind Tunnel as a hover testing facility, rotor performance data were compared with predictions, UH-60 aircraft flight test data, and UH-60 model-scale data from other test facilities. The results indicate that valid hover data for this size rotor can be obtained from this facility at low to medium thrust conditions. Comparisons with flight test and model-scale data demonstrate the variability between existing data sets. Predictions show good agreement with full-scale data. To evaluate the analytical modeling in the 0 to 80 knot speed range, forward flight rotor performance data were acquired and compared with predictions. Comparisons were also made with existing model-scale and flight test data. Power calculations show fair to good agreement with full-scale wind tunnel data at advance ratios between 0.10 to 0.19 and poor agreement at advance ratios below 0.10. Comparisons with flight test and model-scale data show good agreement at all advance ratios tested. Propulsive force calculations show good correlation with full-scale wind tunnel data at advance ratios of 0.10 to 0.19.
机译：完整的四叶片UH-60转子系统在NASA Ames 80-120英尺风洞中进行了测试。已获得低前进速度（0至80节）下的质量数据集，以支持未来的转子开发和分析改进。为了评估NASA Ames 80英尺120英尺风洞作为悬停测试设施，将转子性能数据与预测，UH-60飞机飞行测试数据以及其他测试设施的UH-60模型规模数据进行了比较。结果表明，在中低推力条件下，可以从该设施获得该尺寸转子的有效悬停数据。与飞行测试和模型规模数据的比较证明了现有数据集之间的差异。预测表明与全面数据有很好的一致性。为了评估在0至80节的速度范围内的解析模型，获得了前向飞行旋翼性能数据并将其与预测值进行了比较。还与现有模型规模和飞行测试数据进行了比较。功率计算表明，在0.10至0.19的提前比下，与完整的风洞数据具有良好的一致性，而在低于0.10的提前比下，一致性较差。与飞行测试和模型比例数据的比较表明，在所有测试的提前比率下都具有良好的一致性。推进力计算显示出与全比例风洞数据具有良好的相关性，推进比为0.10至0.19。

著录项

相似文献

  • 外文文献
  • 中文文献
  • 专利
获取原文

客服邮箱：kefu@zhangqiaokeyan.com

京公网安备：11010802029741号 ICP备案号：京ICP备15016152号-6 六维联合信息科技 (北京) 有限公司©版权所有

  • 客服微信

  • 服务号