Table 4 Comparison of applied numerical solver with previous papers
From: A Parametric study on the effects of winglet cant angle on wing aerodynamics and aeroacoustics
Research | Configuration | Grid type | Applied Numerical Solver | L/D increment |
|---|---|---|---|---|
Current research | Aircraft wing | Hybrid | RANS; \(k-\epsilon\) Realizable | 14.44 % |
Gavrilović et al.14 | Aircraft wing | Unstructured | RANS; \(k-\epsilon\) Realizable | 14.29 % |
Vaezi et al.44 | Aircraft wing | Hybrid | RANS; \(k-\omega\) SST | 14.51 % |
Panagiotou et al.35 | Aircraft wing | Hybrid | RANS; Spalart-Allmaras | 15.37 % |
Guerrero et al.17 | Aircraft wing | Hybrid | RANS; \(k-\omega\) SST | Not applicable |
Jiang et al.19 | Turbine blade | Structured | RANS; \(k-\omega\) Standard | Not applicable |
Ye et al.49 | Axial fan | Hybrid | RANS; \(k-\epsilon\) Realizable | Not applicable |
