Wind tunnel performance results of an aeroelastically scaled 2/9 model of the PTA flight test prop-fan
Author:
Affiliation:
1. NASA, Lewis Research Center, Cleveland, OH
2. NASA, Lewis Research Center; Sverdrup Technology, Inc., Cleveland, OH
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.1987-1893
Cited by 6 articles. 订阅此论文施引文献 订阅此论文施引文献，注册后可以免费订阅5篇论文的施引文献，订阅后可以查看论文全部施引文献
1. 3D Flow Features in the Boundary Layer of a Rotating Propeller Blade;AIAA Aviation 2019 Forum;2019-06-14
2. Evaluation of Acoustic Frequency Methods for the Prediction of Propeller Noise;AIAA Journal;2019-06
3. Effect of Rotation on the 3D Boundary Layer around a Propeller Blade;23rd AIAA/CEAS Aeroacoustics Conference;2017-06-02
4. Applicability of Early Acoustic Theory for Modern Propeller Design;23rd AIAA/CEAS Aeroacoustics Conference;2017-06-02
5. Low-speed wind tunnel performance of high-speed counterrotation propellers at angle-of-attack;25th Joint Propulsion Conference;1989-07-12
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