Abstract
Turbulent transonic flow past flattened aerodynamic surfaces is investigated numerically using the RANS equations. The study is focused on: (a) instability of the entire flow structure which eventually results in flow bifurcations, (b) a buffet onset caused by instability of the shock wave/ boundary layer interaction. For a symmetric airfoil at zero angle of attack, computations reveal both bifurcations and buffet in a range of the freestream Mach number M∞. For a Whitcomb type airfoil, computations show greater stability of the flow structure and separated boundary layers. Axisymmetric flow past axisymmetric bodies is also considered, and instability of the flow structure at certain freestream Mach numbers is shown.
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