極厚デルタ形状リフティングボディーの超音速大迎角空力特性

• SUZUKI Kojiro

  東京大学

• TANABE Yoshichika

  東京大学 三菱重工業株式会社

• YAMADA Kazuhiko

  東京大学

• KOSHINO Katsuichiro

  東京大学

• HONGOH Motoyuki

  宇宙科学研究所

Bibliographic Information

Other Title

• ゴクアツ デルタ ケイジョウ リフティングボディー ノ チョウオンソクダイゲイカク クウリキ トクセイ

Abstract

The supersonic aerodynamic characteristics of lifting bodies with blunt thick delta configuration at high angles of attack are experimentally investigated by using the transonic and supersonic wind tunnels. The results show that the lift-to-drag ratio at the trimmed attack angle can be enhanced by the use of the bent nose and body flaps. Significant temporal nonperiodic fluctuation of the aerodynamic force is observed in the narrow freestream range around the Mach number 1. 5 and attack angle 25 deg. The high speed Schlieren pictures reveal that the intermittent breakdown of the leeward vortex pair causes such unsteadiness. This fluctuation can be abbreviated by the combination of the bent nose and the body flaps located on the upper surface of the body.

Journal

• Aeronautical and Space Sciences Japan

  Aeronautical and Space Sciences Japan 48 (561), 549-553, 2000-10-05

  THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

Keywords

• Lifting Body
• High-Angles-of-Attack
• Supersonic Flows
• Unsteady Aerodynamics
• Wind Tunnel Test

Details

• CRID: 1390001288129584256
• NII Article ID: 10004831396
• NII Article ID: 10009364735
• NII Book ID: AN00189072
• DOI: 10.14822/kjsass.48.561_549
• ISSN: 24241369
• ISSN: 00214663
• NDL BIB ID: 5522904
• Web Site: https://ndlsearch.ndl.go.jp/books/R000000004-I5522904
• Text Lang: ja
• Data Source:
  • JaLC
  • NDL
  • CiNii Articles
• Abstract License Flag: Disallowed