Abstract: In this study, flows around generic missiles were computationally modeled and analyzed using a coupled density-based solver, OpenFOAM-HiSA. The issues regarding the modeling procedures, e.g., turbulence modeling, were addressed, and analyses were conducted in subsonic, transonic, and supersonic ranges. The obtained numerical results were compared with the previously published measurements and predictions of other researchers. It was observed that the calculated drag coefficient values were in fairly good agreement with the measurements. Especially, using the SST turbulence model produced better results than using the Spalart-Allmaras model. In addition, the obtained flow pattern was qualitatively similar to the previously published calculation data. With this validated model, the flow field and the drag variation with respect to the freestream Mach number were investigated. Furthermore, the flow around a modified missile geometry was analyzed, and the results were examined comparatively. Hence, the drag reduction mechanism due to geometric modifications could be explained.

Keywords: Missile, High-Speed, Drag, CFD, RANS, OpenFOAM, HiSA

Pages: 129-138