TY - GEN
T1 - Transonic flow field analysis of a free flight capsule using ballistic range
AU - Kiritani, Hideki
AU - Tanaka, Naoki
AU - Ohtani, Kiyonobu
AU - Fujita, Koji
AU - Nagai, Hiroki
N1 - Funding Information:
This work was partially supported by a Grant-in-Aid for Scientific Research (A) Grant Number 17H03474, and it was carried out as part of collaborative research on a specific subject by ISAS/JAXA.
Publisher Copyright:
© 2020, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2020
Y1 - 2020
N2 - The free-flight test of the capsule has been performed using a ballistic range at a Mach number of between 0.77 and 1.52 to visualize a flow field around a capsule. The test models are Hayabusa capsule models whose diameters are 15 mm and 3 mm, and the Schlieren method is used for flow visualization. The characteristics of the flow around the capsule with the 15mm capsule model were investigated using the time-averaged flow field and instantaneous field images. Then, Dynamic Mode Decomposition analysis of the flow field was conducted, it was found that the recompression shock wave and the large fluctuation of the wake are dominant structures in the capsule flow at a Mach number of 1.0. Furthermore, the recompression shock wave fluctuated at Strouhal number of O(0.01) with the 3 mm capsule model test, which indicated that the fluctuation of the recompression shock wave is caused by the local shock wave generated from the free shear layer in the recirculation region.
AB - The free-flight test of the capsule has been performed using a ballistic range at a Mach number of between 0.77 and 1.52 to visualize a flow field around a capsule. The test models are Hayabusa capsule models whose diameters are 15 mm and 3 mm, and the Schlieren method is used for flow visualization. The characteristics of the flow around the capsule with the 15mm capsule model were investigated using the time-averaged flow field and instantaneous field images. Then, Dynamic Mode Decomposition analysis of the flow field was conducted, it was found that the recompression shock wave and the large fluctuation of the wake are dominant structures in the capsule flow at a Mach number of 1.0. Furthermore, the recompression shock wave fluctuated at Strouhal number of O(0.01) with the 3 mm capsule model test, which indicated that the fluctuation of the recompression shock wave is caused by the local shock wave generated from the free shear layer in the recirculation region.
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U2 - 10.2514/6.2020-1990
DO - 10.2514/6.2020-1990
M3 - Conference contribution
AN - SCOPUS:85092353788
SN - 9781624105951
T3 - AIAA Scitech 2020 Forum
BT - AIAA Scitech 2020 Forum
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Scitech Forum, 2020
Y2 - 6 January 2020 through 10 January 2020
ER -