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titleA Study on the Performance of the Fluidic Thrust Vector Control Utilizing Supersonic Coanda Effects
Author(jpn)Song, MyungJun; Yoon, SangHun; Chang, HongBeen; Cho, YongHo; Lee, Yeol
Author(eng)Song, MyungJun; Yoon, SangHun; Chang, HongBeen; Cho, YongHo; Lee, Yeol
Author Affiliation(jpn)Graduate School, Department of Aerospace & Mechanical Engineering, Korea Aerospace University; Graduate School, Department of Aerospace & Mechanical Engineering, Korea Aerospace University; Graduate School, Department of Aerospace & Mechanical Engineering, Korea Aerospace University : Agency for Defense Development; Microfriend Inc.; School of Aerospace & Mechanical Engineering, Korea Aerospace University
Author Affiliation(eng)Graduate School, Department of Aerospace & Mechanical Engineering, Korea Aerospace University; Graduate School, Department of Aerospace & Mechanical Engineering, Korea Aerospace University; Graduate School, Department of Aerospace & Mechanical Engineering, Korea Aerospace University : Agency for Defense Development; Microfriend Inc.; School of Aerospace & Mechanical Engineering, Korea Aerospace University
Issue Date2013-11-30
Publisher宇宙航空研究開発機構(JAXA)
Japan Aerospace Exploration Agency (JAXA)
Publication title宇宙航空研究開発機構特別資料
JAXA Special Publication
VolumeJAXA-SP-13-001E
Start page253
End page261
Publication date2013-11-30
Languageeng
AbstractCo-flow fluidic thrust vector control is one of the efficient thrust-vectoring methods. The present technique controls the direction of a supersonic primary jet by utilizing coanda effects of the secondary jet exhausted at the nozzle exit. A multi-component force measurement system is developed to quantitatively evaluate the performance of the fluidic thrust control technique. Detailed calibration and data analysis have been performed to reduce measurement errors. It is found that the interaction error between load cells possibly introduced by misalignment of the test device is estimated to be less than 5%, and that the unwanted pressure errors associated with air supply tubes are negligible. Some preliminary thrust-vectoring test results and comparison with the results of flow visualization/numerical calculation are also provided. It is observed that the deflection angle the primary jet varies almost linearly with variation of the momentum ratio of the primary jet to the secondary coanda jet.
Description形態: カラー図版あり
Meeting Information: 5th Symposium on Integrating CFD and Experiments in Aerodynamics (October 3-5, 2012, Chofu Aerospace Center, Japan Aerospace Exploration Agency (JAXA)), Chofu, Tokyo, Japan
Physical characteristics: Original contains color illustrations
Keywordssupersonic; thrust vector control; coanda effects; calibration
Document TypeConference Paper
JAXA Category特別資料
NASA Subject CategoryAerodynamics
ISSN1349-113X
NCIDAA11984031
SHI-NOAA0062070020
Report NoJAXA-SP-13-001E
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/15354


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