Control surface effectiveness of low Reynolds number flight vehicles

• ANYOJI Masayuki

  Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency

• OKAMOTO Masato

  Department of Aeronautics, Kanazawa Institute of Technology

• HIDAKA Hidenori

  Department of Aeronautics, Kanazawa Institute of Technology

• KONDO Katsutoshi

  Department of Mechanical Engineering, Tokyo University of Science

• OYAMA Akira

  Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency

• NAGAI Hiroki

  Department of Aerospace Engineering, Tohoku University

• FUJII Kozo

  Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency

Abstract

Low-speed wind tunnel tests are carried out to investigate the control surface effectiveness at low Reynolds numbers (Re = 20,000-80,000). A thick airfoil, NACA0012, has a nonlinearity of the control surface effectiveness, which are associated with flow separation both on the upper and lower surfaces and a formation of a laminar separation bubble. Thin airfoils such as NACA0006 and a 3%c flat plate have a much smaller nonlinearity of the control surface effectiveness. These differences in the control surface effectiveness are due to the nonlinearity of the lift curve for each airfoil, and the flow separation behavior has a profound effect on the control surface effectiveness.

Journal

• Journal of Fluid Science and Technology

  Journal of Fluid Science and Technology 9 (5), JFST0072-JFST0072, 2014

  The Japan Society of Mechanical Engineers

Keywords

• Low Reynolds number
• Control surface effectiveness
• Flap deflection
• Flow separation
• Nonlinearity
• Airfoil thickness

Details

• CRID: 1390001205245318912
• NII Article ID: 130004705259
• DOI: 10.1299/jfst.2014jfst0072
• ISSN: 18805558
• Web Site: https://www.jstage.jst.go.jp/article/jfst/9/5/9_2014jfst0072/_pdf
• Text Lang: en
• Data Source:
  • JaLC
  • Crossref
  • CiNii Articles
  • KAKEN
• Abstract License Flag: Disallowed