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 below.

Mach 9.59 HB-2 geometry at 0° angle-of-attack: Surface heat transfer.

A comparison between the current results (IBL), experimental data (Exp.) and a higher-fidelity Navier-Stokes computation (NBS) is presented in the following figure, which shows a good match between the three methods.

Mach 9.59 HB-2 geometry at 0° angle-of-attack: Comparison of surface heat transfer with higher-fidelity method (NBS) and Experimental data from ....

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)"