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RESEARCH ON DELTA WING UNSTEADY HIGH ANGLE OF ATTACK AERODYNAMICS

Research Project

Project/Area Number 06452343
Research Category

Grant-in-Aid for Scientific Research (B)

Allocation TypeSingle-year Grants
Section一般
Research Field Aerospace engineering
Research InstitutionThe University of Tokyo

Principal Investigator

SATO Junzo  The University of Tokyo Graduate School of Engineering, Professor, 大学院・工学系研究科, 教授 (80011211)

Co-Investigator(Kenkyū-buntansha) TATSUMI Kaoru  The University of Tokyo Graduate School of Engineering, Assistant, 大学院・工学系研究科, 助手 (40236550)
SUNADA Yasuto  The University of Tokyo Graduate School of Engineering, Assistant, 大学院・工学系研究科, 助手 (50216488)
RINOIE Kenichi  The University of Tokyo Graduate School of Engineering, Associate Professor, 大学院・工学系研究科, 助教授 (20175037)
Project Period (FY) 1994 – 1996
Project Status Completed (Fiscal Year 1996)
Budget Amount *help
¥7,400,000 (Direct Cost: ¥7,400,000)
Fiscal Year 1996: ¥700,000 (Direct Cost: ¥700,000)
Fiscal Year 1995: ¥2,400,000 (Direct Cost: ¥2,400,000)
Fiscal Year 1994: ¥4,300,000 (Direct Cost: ¥4,300,000)
KeywordsDelta wing / Vortex / High Angles of Attack / Unsteady Aerodynamics
Research Abstract

This research is to study the basic physical details of the fluid dynamic phenomena associated with the wing rock observed at hjgh angles of attack on delta wings. A specially designed forced roll oscillation method with a two-components balance was introduced to take the aerodynamic force and moment ; not adopting the conventional free rotation methods. The success of the method depends on the accurate separation of the inertial and aerodynamic forces from the measurement. Use of light weight models, low rate of oscillation and elaborate calibration of balances made it possible to get data up to the non-dimensional roll rate of 0.1.
Two delta wing models of 14 and 7 degree semi-apex angle, respectively, are put to the tests and the model with a smaller apex angle shows very complicated aerodynamics. The reason of these changes are mode clear in relation to the vortex breakdown and vortex splitting by comparing the blance outputs with the flow visualization pictures.

Report

(4 results)
  • 1996 Annual Research Report   Final Research Report Summary
  • 1995 Annual Research Report
  • 1994 Annual Research Report

Research Products

(4 results)

All Other

All Publications (4 results)

  • [Publications] 郭東潤: "ロールするデルタ翼の非定常空気力に関する研究" 日本航空宇宙学会誌. 45(印刷中). (1997)

    • Description
      「研究成果報告書概要(和文)」より
    • Related Report
      1996 Final Research Report Summary
  • [Publications] Dong Toun Kwak, et al.: "Experimental Research on Unsteady Aerodynamics of Rolling Delta Wings" Journal of the Japan Society for Aeronautical and Space Sciences. Vol. 45, No. 519, (in press.). (1997)

    • Description
      「研究成果報告書概要(欧文)」より
    • Related Report
      1996 Final Research Report Summary
  • [Publications] 郭東潤: "ロールするデルタ翼の非定常空気力に関する研究" 日本航空宇宙学会誌. 45(印刷中). (1997)

    • Related Report
      1996 Annual Research Report
  • [Publications] 郭東潤: "1995 Japan-China Joint Symposium on Advanced Energy and Transportation Engineering, A Collection of Technical Papers" 佐藤淳造,韓肇元, 272 (1995)

    • Related Report
      1995 Annual Research Report

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Published: 1994-03-31   Modified: 2016-04-21  

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