1/3/2023 0 Comments Naca 0012 airfoil![]() Acoustic measurements were conducted in an anechoic wind tunnel using a stationary NACA 0012 airfoil at 0° pitch angle. ![]() The NACA 0012 is symmetrical airfoil with no camber and 12% thickness to chord length ratio. Some interesting features in the surface pressure distributions along the airfoil are found for these low-Reynolds-number flows.Trailing edge noise from stationary and rotating NACA 0012 airfoils is characterised and compared with a noise prediction based on the semi-empirical Brooks, Pope, and Marcolini (BPM) model. The computed density and velocity flowfields are compared with experimental data and found to be in generally good agreement. Because of problems with this method at the low subsonic condition, caused by excessive statistical fluctuations, a new particle method called the information preservation technique is applied. For the supersonic and transonic cases, the particle method employed is the direct simulation Monte Carlo method. In all three cases, the continuum approach solves the Navier-Stokes equations with a slip boundary condition on the airfoil surface. Three different conditions are considered: supersonic, transonic, and low subsonic. Some interesting features in the surface pressure distributions along the airfoil are found for these low-Reynolds-number flows.ĪB - Rarefied gas flows around a NACA 0012 airfoil are simulated using both particle and continuum approaches. ![]() N2 - Rarefied gas flows around a NACA 0012 airfoil are simulated using both particle and continuum approaches. T1 - Computation of rarefied gas flows around a NACA 0012 airfoil ![]()
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