Transonic Flow over the ONERA M6 Wing
Application ID: 105731
This example demonstrates how to set up the classical external-flow problem of solving for the high-speed, compressible, turbulent flow over the ONERA-M6 wing. The problem involves finding a steady-state solution of the flow field around the 3D, swept wing geometry, immersed in a transonic flow at a moderately high angle of attack. The solution indicates the formation of weak shocks on the upper surface of the wing.
Disclaimer: This model uses data from the ONERA-M6 wing as a reference. This model is not affiliated with, endorsed by, or sponsored by ONERA.
This model example illustrates applications of this type that would nominally be built using the following products:
however, additional products may be required to completely define and model it. Furthermore, this example may also be defined and modeled using components from the following product combinations:
The combination of COMSOL® products required to model your application depends on several factors and may include boundary conditions, material properties, physics interfaces, and part libraries. Particular functionality may be common to several products. To determine the right combination of products for your modeling needs, review the Tabella delle Funzionalità and make use of a free evaluation license. The COMSOL Sales and Support teams are available for answering any questions you may have regarding this.