E. N. TINOCO; O. P. BRODERSEN; S. KEYE; K. R. LAFLIN; J. C. VASSBERG; B. RIDER; R. A. WAHLS; J. H. MORRISON; B. W. POMEROY; D. HUE; M. MURAMA; R. NANGIA

DOI Number: 10.13009/EUCASS2023-055

Results from the Seventh AIAA CFO Drag Prediction Workshop -Expanding the Envelope -are presented. These cases focused on force/moment and pressure predictions for the NASA Common Research Model wing-body configuration. The Common Research Model geometry was deformed to the appropriate static aeroelastic twist and deflection at each specified angle-of-attack. The grid refinement study (Case 1) used a common set of overset, multiblock structured, and unstructured grids, as well as user created unstructured and structured based grids. Solutions were requested for the wing-body at a fixed Mach number and lift coefficient near buffet onset. The wing-body static aeroelastic/buffet study (Case 2) specified an angle-of-attack sweep at finely spaced intervals through the zone where wing shock-induced separation was expected to begin. Case 3 requested a Reynolds number/dynamic pressure sweep at a constant lift coefficient. The optional Case 4 requested grid adaption solutions of the wing-body at a specified flight condition. Optional Case 5 requested solutions beyond steady RANS. Optional Case 6 requested coupled aerostructural wing-body solutions. Results from this workshop highlight the progress made since the last workshop in 2016, and the continuing need for CFD improvement, particularly for conditions with significant flow separation, and close to buffet onset. These comparisons also suggest the need for improved experimental diagnostics to guide future CFD development.

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In Categories: 1. Aerospace Europe Conference 2023, 1.Events, 15. Sustainable Aviation
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