LES computation of turbulent heat flux on reentry capsule afterbody with forced transition

Tomoaki Ishihara, Yousuke Ogino, Naofumi Ohnishi, Hideyuki Tanno

Research output: Chapter in Book/Report/Conference proceedingConference contributionpeer-review

1 Citation (Scopus)


A high order CFD code was developed for LES computation of turbulent heat flux in hypersonic flow. Aeroheating measurement tests with forced transition on an Apollo capsule model and an HTV-R which was a manned space capsule under development by JAXA were performed by the free-piston shock tunnel HIEST in JAXA Kakuda Space Center. Measured data set indicate that heat flux on the forebody of the Apollo capsule model was 1.5-2 times larger than one in laminar flow. On the other hand, the heat flux on the afterbody of HTV-R became significantly larger. Furthermore, in the separation region which exists afterbody of capsules, the Baldwin-Lomax model which can reproduce turbulent heat flux in the attached flow, tends to underestimate. In order to reproduce the turbulent heat flux on the after body by numerical simulation, high order CFD code towards LES in hypersonic flow is needed. Since the robustness near the shock and high resolution in the boundary layer is needed for LES in hypersonic flow, improved WENO method is employed. We calculated the hypersonic flow (M∞ = 17) around cylinder and investigated the robustness for strong shock by the method. Smooth pressure distribution was obtained agree well with the calculated heat flux by NASA LAURA code. Our developed code applied to the hypersonic flowfield around HTV-R with a trip and the heat flux was examined.

Original languageEnglish
Title of host publication53rd AIAA Aerospace Sciences Meeting
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624103438
Publication statusPublished - 2015
Event53rd AIAA Aerospace Sciences Meeting, 2015 - Kissimmee, United States
Duration: 2015 Jan 52015 Jan 9

Publication series

Name53rd AIAA Aerospace Sciences Meeting


Conference53rd AIAA Aerospace Sciences Meeting, 2015
Country/TerritoryUnited States


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