Transonic flow field analysis of a free flight capsule using ballistic range

Hideki Kiritani, Naoki Tanaka, Kiyonobu Ohtani, Koji Fujita, Hiroki Nagai

Research output: Chapter in Book/Report/Conference proceedingConference contribution

1 Citation (Scopus)


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.

Original languageEnglish
Title of host publicationAIAA Scitech 2020 Forum
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624105951
Publication statusPublished - 2020
EventAIAA Scitech Forum, 2020 - Orlando, United States
Duration: 2020 Jan 62020 Jan 10

Publication series

NameAIAA Scitech 2020 Forum
Volume1 PartF


ConferenceAIAA Scitech Forum, 2020
Country/TerritoryUnited States

ASJC Scopus subject areas

  • Aerospace Engineering


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