Publikationsdatum:
2019-07-13
Beschreibung:
A domain decomposition method is developed for solving the aerodynamic/aeroacoustic problem of an airfoil in a vortical gust. The computational domain is divided into inner and outer regions wherein the governing equations are cast in different forms suitable for accurate computations in each region. Boundary conditions which ensure continuity of pressure and velocity are imposed along the interface separating the two regions. A numerical study is presented for reduced frequencies ranging from 0.1 to 3.0. It is seen that the domain decomposition approach in providing robust and grid independent solutions.
Schlagwort(e):
Numerical Analysis
Materialart:
NASA/TM-2002-212010
,
NAS 1.15:212010
,
E-13699
,
AIAA Paper 2003-0883
,
41st Aerospace Sciences Meeting and Exhibit; Jan 06, 2003 - Jan 09, 2003; Reno, NV; United States
Format:
application/pdf
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