­
­
­
­

Inventi Impact - Aerospace Engineering

Articles

  • Inventi:eae/52/14
    WIND TUNNEL TESTING ON START/UNSTART CHARACTERISTICS OF FINITE SUPERSONIC BIPLANE WING
    Hiroshi Yamashita, Naoshi Kuratani, Masahito Yonezawa, Toshihiro Ogawa, Hiroki Nagai, Keisuke Asai, Shigeru Obayashi

    This study describes the start/unstart characteristics of a finite and rectangular supersonic biplane wing. Two wing models were tested in wind tunnels with aspect ratios of 0.75 (model A) and 2.5 (model B). The models were composed of a Busemann biplane section. The tests were carried out using supersonic and transonic wind tunnels over a Mach number range of 0.3 = ??8 = 2.3 with angles of attack of 0°, 2°, and 4°. The Schlieren system was used to observe the flow characteristics around the models. The experimental results showed that these models had start/unstart characteristics that differed from those of the Busemann biplane (two dimensional) owing to three-dimensional effects.Models A and B started at lowerMach numbers than the Busemann biplane. The characteristics also varied with aspect ratio: model A (1.3 < ??8 < 1.5) started at a lower Mach number than model B (1.6 < ??8 < 1.8) owing to the lower aspect ratio. Model B was located in the double solution domain for the start/unstart characteristics at??8 = 1.7, and model B was in either the start or unstart state at??8 = 1.7. Once the state was determined, either state was stable.

    How to Cite this Article
    CC Compliant Citation: Hiroshi Yamashita, Naoshi Kuratani, Masahito Yonezawa, et al., “Wind Tunnel Testing on Start/ Unstart Characteristics of Finite Supersonic Biplane Wing,” International Journal of Aerospace Engineering, vol. 2013, Article ID 231434, 10 pages, 2013. doi:10.1155/2013/231434.
    Download Full Text