CFD Validation of Shock-Shock Interaction Flow Fields

Current capabilities for numerical simulation of laminar shock-shock interactions are examined. Two fundamental configurations are considered: the Edney IV shock-shock interaction and the crossing oblique-shock interaction generated by a double wedge configuration. Two cases for each configuration were examined by a distinguished group of international researchers using the Reynolds-averaged Navier-Stokes (RANS) equations and Direct Simulation Monte Carlo (DSMC) methods. The report presents an extensive comparison of the submitted computations and experimental data. INTRODUCTION Accurate prediction of the flow field resulting from the interaction of shock waves is critical for the design of efficient air-breathing hypersonic vehicles. In an effort to advance hypersonicvehicle related technologies the NATO Research Technology Organization (RTO) Advanced Vehicle Technology Panel Working Group 10 (WG 10) has examined the current state-of-the-art in numerical simulations. The following report summarizes the work of the CFD validation subgroup of WG 10 in the area of validation of numerically simulated laminar shock-shock interactions. Two geometrically simple, yet computationally challenging, flow fields were chosen for this study. The first is the well-known Edney type IV interaction [1] that can result in extreme pressure and heat loads. The second is the flow field resulting from crossing oblique shocks generated by opposing wedges. While on the surface this interaction appears rather simple, in the dual-solution domain, [2] between the theoretical Neumann and detachment conditions, both regular and irregular reflections are possible and hysteresis in the reflection configuration has been observed. Two test cases for each of the interactions described above were characterized experimentally and numerically simulated during the course of the WG 10 effort. The remainder of this manuscript describes the results for first the Edney IV interaction and then the crossing oblique-shock interaction. EDNEY IV SHOCK-SHOCK INTERACTION The heating rates generated by shock-shock interactions can result in some of the most severe heating loads imposed on the thermal protection systems of hypersonic lifting bodies and air-breathing propulsion systems. In regions near a leading edge heating levels up to 30 times those encountered in an undisturbed stagnation * Program Manager, Currently Special Assistant DDR&E, Assoc. Fellow AIAA. † Program Manager, Senior Member AIAA. Report Documentation Page Form Approved OMB No. 0704-0188 Public reporting burden for the collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden, to Washington Headquarters Services, Directorate for Information Operations and Reports, 1215 Jefferson Davis Highway, Suite 1204, Arlington VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to a penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number. 1. REPORT DATE 01 JAN 2006 2. REPORT TYPE N/A 3. DATES COVERED 4. TITLE AND SUBTITLE CFD Validation of Shock-Shock Interaction Flow Fields 5a. CONTRACT NUMBER