An objective of the PAW6 inlet test case is to assess the ability and accuracy of existing computer codes and modeling techniques for a mixed-compression inlet with an internal shock structure, porous bleed region, and vortex generators. The inlet test case being investigated for PAW-6 is referred to as the NASA 1507 inlet, which is a Mach 3 axisymmetric-spike, mixed-compression inlet that was tested at the NASA Ames supersonic wind tunnel in the late 1960s. The NASA 1507 inlet presents a challenging test case due to the high Mach number, internal supersonic compression, porous bleed regions, internal terminal shock structure, and vortex generators present in the flow. Note that, in contrast to previous workshop test cases, the wind-tunnel data is known and provided to participants prior to the workshop. The inlet test case files including the participant guide, inlet geometry, computational grids, data submission file, and an excel file providing additional details can be downloaded using the link below.
12/02/2022 UPDATE: Results Spreadsheet Available for Download Below
The spreadsheet linked below should be used for submitting inlet data.
Download Results Spreadsheet v3.0
10/20/2022 UPDATE: Updated Grids Available for Download Below
Previous version of the inlet grids included an incorrect surface definition for the nozzle portion of the geometry. The updated files can be downloaded using the links below.
Download Inlet Participant Document and Structured Grids
Unstructured, mixed-element grids generated using the Pointwise software are being provided to participants for three levels of refinements and for inlet configurations C and D. The unstructured grids can be downloaded using the links provided below.
Download Coarse Grids for Configurations B, C, and D