title: Development of an aerodynamic measurement system for hypersonic rarefied flows.
abstract: A hypersonic rarefied wind tunnel (HRWT) has lately been developed at Japan Aerospace Exploration Agency in order to improve the prediction of rarefied aerodynamics. Flow characteristics of hypersonic rarefied flows have been investigated experimentally and numerically. By conducting dynamic pressure measurements with pendulous models and pitot pressure measurements, we have probed flow characteristics in the test section. We have also improved understandings of hypersonic rarefied flows by integrating a numerical approach with the HRWT measurement. The development of the integration scheme between HRWT and numerical approach enables us to estimate the hypersonic rarefied flow characteristics as well as the direct measurement of rarefied aerodynamics. Consequently, this wind tunnel is capable of generating 25 mm-core flows with the free stream Mach number greater than 10 and Knudsen number greater than 0.1.
authors: Japan Aerospace Exploration Agency, Tokyo 182-8522, Japan.
authors: T
authors: T
authors: Ozawa
authors: Japan Aerospace Exploration Agency, Tokyo 182-8522, Japan.
authors: K
authors: K
authors: Fujita
authors: Japan Aerospace Exploration Agency, Tokyo 182-8522, Japan.
authors: T
authors: T
authors: Suzuki