A study on active flow control for next-generation SST for higher L/D

S. Aso, M. Kamishita, K. Karashima, K. Sato

研究成果: 著書/レポートタイプへの貢献会議での発言

6 引用 (Scopus)

抄録

An experimental study on the improvement of aerodynamic characteristics of an arrow wing by lateral blowing in low and high speed flows, has been conducted. An arrow wing [1,2], which is one of the baseline configurations of next-generation SST, is selected for the experiments. As compared to the delta wing, it is known that an arrow wing has higher the ratio of lift to drag and improvement of stability in low speed region because of the supersonic leading edge. However, for better and cost effective configurations higher L/D is requested for the development of SST. The testing model is the combination of a body of a circular cylinder and conical apex and a modified arrow wing with aspect ratio of 1.91. The lateral blowing is realized by injecting a pair of steady jets in a direction parallel to the trailing edge of the wing. The experiments have been performed in the transonic and supersonic wind tunnel located at ISAS under the testing conditions of M∞(free-stream Mach number) of 0.3 ~2.3, Re unit (unit Reynolds number) of 1.06×107~3.10× 107 [1/m], angle of attack of -15°~30° and Cj (jet momentum coefficient) of 0.0084 ~0.0316. The results show that the CL and L/D is increased by lateral blowing while CD is slightly increased for positiveangle of attack. The results suggest that the lateral blowing can be useful for the improvement of aerodynamic characteristics of the arrow wing in low and high speed flows.

元の言語英語
ホスト出版物のタイトル32nd AIAA Fluid Dynamics Conference and Exhibit
出版物ステータス出版済み - 12 1 2002
イベント32nd AIAA Fluid Dynamics Conference and Exhibit 2002 - St. Louis, MO, 米国
継続期間: 6 24 20026 26 2002

出版物シリーズ

名前32nd AIAA Fluid Dynamics Conference and Exhibit

その他

その他32nd AIAA Fluid Dynamics Conference and Exhibit 2002
米国
St. Louis, MO
期間6/24/026/26/02

Fingerprint

Flow control
Blow molding
Aerodynamics
Testing
Circular cylinders
Angle of attack
Mach number
Wind tunnels
Drag
Aspect ratio
Momentum
Reynolds number
Experiments
Costs

All Science Journal Classification (ASJC) codes

  • Engineering (miscellaneous)
  • Aerospace Engineering

これを引用

Aso, S., Kamishita, M., Karashima, K., & Sato, K. (2002). A study on active flow control for next-generation SST for higher L/D. : 32nd AIAA Fluid Dynamics Conference and Exhibit (32nd AIAA Fluid Dynamics Conference and Exhibit).

A study on active flow control for next-generation SST for higher L/D. / Aso, S.; Kamishita, M.; Karashima, K.; Sato, K.

32nd AIAA Fluid Dynamics Conference and Exhibit. 2002. (32nd AIAA Fluid Dynamics Conference and Exhibit).

研究成果: 著書/レポートタイプへの貢献会議での発言

Aso, S, Kamishita, M, Karashima, K & Sato, K 2002, A study on active flow control for next-generation SST for higher L/D. : 32nd AIAA Fluid Dynamics Conference and Exhibit. 32nd AIAA Fluid Dynamics Conference and Exhibit, 32nd AIAA Fluid Dynamics Conference and Exhibit 2002, St. Louis, MO, 米国, 6/24/02.
Aso S, Kamishita M, Karashima K, Sato K. A study on active flow control for next-generation SST for higher L/D. : 32nd AIAA Fluid Dynamics Conference and Exhibit. 2002. (32nd AIAA Fluid Dynamics Conference and Exhibit).
Aso, S. ; Kamishita, M. ; Karashima, K. ; Sato, K. / A study on active flow control for next-generation SST for higher L/D. 32nd AIAA Fluid Dynamics Conference and Exhibit. 2002. (32nd AIAA Fluid Dynamics Conference and Exhibit).
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