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Viscous computation

The viscous computation for this tutorial was carried out using the Integral-Boundary-Layer (IBL). The laminar heat flux is shown in the plot

XXXXX Mach 9.59 HB-2 geometry at 15° angle-of-attack: Surface heat transfer.

XXXXX Mach 9.59 HB-2 geometry at 15° angle-of-attack: Surface heat transfer.

The reference experimental data for this test case is from the JAXA Research and Development Report JAXA-RR-04-035E with ISSN 1349-1113 and title: "Comparative Force/Heat Flux Measurements between JAXA Hypersonic Test Facilities Using Standard Model HB-2 (Part 1: 1.27 m Hypersonic Wind Tunnel Results)"