A numerical study of the flow topologies over the 60° delta wing of the AGARD-B model at Mach 0.80 has revealed that vortex bursting occurs between 13°-15° angle of attack, while vortex separation occurs above 18°. These aerodynamic features have been identified as additional comparison criteria which need to be replicated for facilities using the model for calibration or inter-tunnel comparison purposes. The numerical simulations were performed using ANSYS Fluent V13, a structured mesh with near wall treatment and the Spalart-Allmaras and κ-ω SST turbulence models, and validated experimentally in a 5’x5’ transonic facility. Other aspects not previously identified or studied are firstly a recovery shock between the primary and secondary vortex that exists only when vortex bursting occurs, and secondly the lack of a shock between the wing and vortex when the flow topology corresponds to the centreline shock region as observed in other studies.
Tuling, S., Vallabh, B., & Morelli, M. F. (2015). Compressibility effects for the AGARD-B model. Aeronautical Journal, 119(1214), 543-552. https://doi.org/10.1017/S0001924000010605