TY - JOUR
T1 - Is DES approach better than RANS approach for airfoil stall simulation?
AU - Li, Dong
AU - Men'shov, Igor
AU - Nakamura, Yoshiaki
PY - 2006/4
Y1 - 2006/4
N2 - Purpose. DES (Detached-Eddy Simulation) approach is theoretically a good way of taking advantage of the merits of both RANS (Reynolds Averaged Navier-Stokes) and LES (Large Eddy Simulation) approaches. For engineers, it is important to know for a certainty that this is really so. We take the problem of stall and show that DES approach is really good for two of three different types of NACA airfoils. In the full paper, we explain in detail what we did for the problem of stall; here we give only a briefing. Even though LES method is expected for massively separated flow, it is not satisfactory because of the enormous requirement of grid points for practical aviation flow with large Reynolds number. In DES approach, the Spalart-Allmaras turbulence model reduces to a RANS formulation near the wall, and to a subgrid model of LES away from the wall. It is found that: (1) before the stall, DES gets almost the same results as RANS for three airfoils; (2) near the stall, for NACA64A-006 and NACA631-012, DES results are much closer to experimental data than RANS; and for NACA633-018, they are almost the same because it is trailing-edge stall type with small separation region when the stall occurs.
AB - Purpose. DES (Detached-Eddy Simulation) approach is theoretically a good way of taking advantage of the merits of both RANS (Reynolds Averaged Navier-Stokes) and LES (Large Eddy Simulation) approaches. For engineers, it is important to know for a certainty that this is really so. We take the problem of stall and show that DES approach is really good for two of three different types of NACA airfoils. In the full paper, we explain in detail what we did for the problem of stall; here we give only a briefing. Even though LES method is expected for massively separated flow, it is not satisfactory because of the enormous requirement of grid points for practical aviation flow with large Reynolds number. In DES approach, the Spalart-Allmaras turbulence model reduces to a RANS formulation near the wall, and to a subgrid model of LES away from the wall. It is found that: (1) before the stall, DES gets almost the same results as RANS for three airfoils; (2) near the stall, for NACA64A-006 and NACA631-012, DES results are much closer to experimental data than RANS; and for NACA633-018, they are almost the same because it is trailing-edge stall type with small separation region when the stall occurs.
KW - Airfoil stall
KW - Detached-Eddy Simulation (DES)
KW - Spalart-Allmaras turbulence model
UR - http://www.scopus.com/inward/record.url?scp=33745665079&partnerID=8YFLogxK
M3 - 文章
AN - SCOPUS:33745665079
SN - 1000-2758
VL - 24
SP - 228
EP - 231
JO - Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University
JF - Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University
IS - 2
ER -