Abstract
A direct numerical simulation (DNS) algorithm has been developed for use in the investigation of crossflow instability on supersonic swept wings, an application of potential relevance to the design of the High-Speed Civil Transport (HSCT). The fully explicit algorithm exploits high-order compact-difference and spectral-collocation methods to solve the compressible Navier–Stokes equations in body-fitted coordinates. The method is applied to the investigation of stationary crossflow instability on an infinitely long 77-degree swept wing in Mach 3.5 flow. The results of the DNS are compared with the predictions of linear stability theory (LST) and linear parabolized stability equation (PSE) methodology. In general, the independently conducted DNS and PSE investigations agree closely in terms of the growth rate, the structure, and the orientation angle of the predicted stationary crossflow instability. Although further study is warranted for the case of large-amplitude (nonlinear) disturbances, the close agreement between the methods offers preliminary validation of both the DNS and PSE approaches for this application.
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