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首页> 外文期刊>Journal of Spacecraft and Rockets >Drag Behavior of Inflatable Reentry Vehicle in Transonic Regime
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Drag Behavior of Inflatable Reentry Vehicle in Transonic Regime

机译：跨音速条件下的充气再入飞行器阻力特性

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摘要

The drag coefficient for inflatable reentry vehicles shows discrepancies between a wind tunnel experiment and a flight test in a transonic regime. These discrepancies exist in the drag decrease behavior in the transonic regime and local minimum values of drag above the sonic speed in a wind tunnel. Hence, the present paper focuses on uncovering the reasons and mechanisms behind the same and investigates transonic flowfields around a vehicle by using a transonic wind tunnel and the computational fluid dynamics approach. Several test models with diameters ranging from 56 to 96 mm are used to quantitatively evaluate the effects of scale and a sting attached on the rear. Aerodynamic coefficients, pressures at the rear of the model, and density-gradient distributions are measured for operation conditions of freestream Mach numbers ranging between 0.8 and 1.3. In addition, detailed distributions of the flowfield properties are clarified using the computational fluid dynamics method, which is validated by the experimental data. The results indicate that a sting behind the test models reduces the steep drag decrease at transonic speeds and that shock waves reflected on the test-section walls of the wind tunnel result in local minimum values at supersonic speeds.
机译：充气式再入车辆的阻力系数显示了跨音速状态下的风洞实验与飞行测试之间的差异。这些差异存在于跨音速状态下的风阻减小行为和风洞中高于声速的风阻的局部最小值。因此，本文着重于揭示其背后的原因和机理，并通过使用跨音速风洞和计算流体动力学方法研究车辆周围的跨音速流场。几种直径从56到96毫米的测试模型用于定量评估水垢和后部附着的st的影响。针对自由流马赫数在0.8到1.3之间的运行条件，测量了空气动力学系数，模型后部的压力以及密度梯度分布。此外，使用计算流体动力学方法阐明了流场特性的详细分布，并通过实验数据进行了验证。结果表明，测试模型后面的刺痛降低了跨音速下的急剧阻力减小，并且风洞的测试截面壁上反射的冲击波导致了超音速下的局部最小值。

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  • 来源
    《Journal of Spacecraft and Rockets》 |2019年第2期|577-585|共9页
  • 作者

    Takahashi Yusuke; Matsunaga Manabu; Oshima Nobuyuki; Yamada Kazuhiko;

  • 作者单位

    Hokkaido Univ, Fac Engn, Kita Ku, Kita 13 Nishi 8, Sapporo, Hokkaido 0608628, Japan;

    Hokkaido Univ, Grad Sch Engn, Kita Ku, Kita 13 Nishi 8, Sapporo, Hokkaido 0608628, Japan|IHI Corp, Tokyo, Japan;

    Hokkaido Univ, Fac Engn, Kita Ku, Kita 13 Nishi 8, Sapporo, Hokkaido 0608628, Japan;

    Japan Aerosp Explorat Agcy JAXA, Inst Space & Astronaut Sci, Chuo Ku, 3-1-1 Yoshinodai, Sagamihara, Kanagawa 2525210, Japan;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
  • 原文格式 PDF
  • 正文语种 eng
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