Influence of Partial Electrical Conducting Wall on Electrodynamic Flow Control

Author:

NAGATA Yasunori1,YAMANE Eisuke1,NORII Takumi1,KOUCHI Toshinori1,YANASE Shinichiro1

Affiliation:

1. Graduate School of Natural Science and Technology, Okayama University

Publisher

Japan Society for Aeronautical and Space Sciences

Reference14 articles.

1. 1) Suzuki, K.: Aerothermodynamic Studies on Low-Ballistic-Coefficient Mars Aerocapture Vehicle with Drag Modulation and Electric Propulsion, Trans. Jpn. Soc. Aeronaut. Space Sci., 16 (2018), pp. 412–419.

2. 2) Ziemer, R. W. and Bush, W. B.: Magnetic Field Effects on Bow Shock Stand-off Distance, Phys. Rev. Lett., 1 (1958), pp. 58–59.

3. 3) Bush, W. B.: Magnetohydrodynamic-Hypersonic Flow Past a Blunt Body, J. Aero/Space Sci., 25 (1958), pp. 685–690.

4. 4) Kawamura, M., Nagata, Y., Katsurayama, H., Otsu, H., Yamada, K., and Abe, T.: Magnetoaerodynamic Force on a Magnetized Body in a Partially Ionized Flow, J. Spacecraft Rockets, 50 (2013), pp. 347-351.

5. 5) Nagata, Y., Satofuka, Y., Watanabe, Y., Tezuka, A., Yamada, K., and Abe, T.: Experimental Study on the Magneto-aerodynamic Force Deflected by Magnetic Field Interaction in a Weakly-ionized Plasma Flow, AIAA Paper 2013-2999, 2013.

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