Predictions using the launch ascent and vehicle aerodynamics (LAVA) solver framework for the NASA shock–plume interaction biconvex model and C608 supersonic aircraft prototype geometries are compared in support of the Third AIAA Sonic Boom Prediction workshop. Descriptions of the mesh generation techniques and numerical methods are provided along with a comparison of near-field and far-field predictions with available experimental data as well as other workshop submissions. Strong agreement was observed between the LAVA structured curvilinear and unstructured solver near-field predictions for the biconvex model and the C608 aircraft: predictions that were also compared against validation and verification data. Additionally, near-field and far-field ground signature results using the combination of a truncated computational fluid dynamics (CFD) domain coupled to a midfield space marching method and propagated to the ground using sBOOM will be discussed. This approach is shown to provide an efficient way to propagate near-field pressure signatures to the ground with the same accuracy as the near-field CFD coupled to sBOOM but at less computational cost.
Structured and Unstructured Simulations for the Third AIAA Sonic Boom Prediction Workshop
Journal of Aircraft ; 59 , 3 ; 624-646
2021-10-26
23 pages
Article (Journal)
Electronic Resource
English