Numerical simulations have been conducted to simulate the flow over an oscillating NACA 0012 airfoil operating at various Mach numbers, oscillatory frequencies and mean angles of attack, for nominally attached flow conditions. The simulations have been carried out using the ANSYS-CFX5 flow solver, to assess the performance of this tool in conducting unsteady aerodynamic analysis of this nature. Numerical results are compared to the experimental work of Landon, and discussed in relation to previous numerical studies. Overall a good agreement is found for the majority of cases, however, a number of discrepancies have been noted and discussed, particularly regarding simulation of high mean incidence angles and subsonic Mach numbers.

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