Aerodynamic Analysis of Manta Ray …
313
(a) Zimmerman model
(b) Manta A and Manta B
Fig. 1 Wing planforms
(a) Computational Domain
(b) Meshed Cylindrical Domain
(c) Number of Nodes(N) vs C D
(d) C L vs C D
Fig. 2 Computational domain, meshing, grid convergence study and validation
diameter of the domain were about 10 times and 5 times of the root chord, respectively.
Unstructured grid was generated in the domain along with 10 prism layers near the
body as noted in Fig. 2b and the first layer height is 3×10
5 m to maintain wall y+
less than 1. Velocity inlet, pressure outlet, symmetry and wall boundary conditions
were applied at the various domain boundaries. The CFD analysis was conducted at
313
(a) Zimmerman model
(b) Manta A and Manta B
Fig. 1 Wing planforms
(a) Computational Domain
(b) Meshed Cylindrical Domain
(c) Number of Nodes(N) vs C D
(d) C L vs C D
Fig. 2 Computational domain, meshing, grid convergence study and validation
diameter of the domain were about 10 times and 5 times of the root chord, respectively.
Unstructured grid was generated in the domain along with 10 prism layers near the
body as noted in Fig. 2b and the first layer height is 3×10
5 m to maintain wall y+
less than 1. Velocity inlet, pressure outlet, symmetry and wall boundary conditions
were applied at the various domain boundaries. The CFD analysis was conducted at