CFD Gallery

This problem represents a parachute in a Mach 2 flow field. The unstructured axisymetric grid contains 18,028 nodes and 17,601 cells. Shown in the figure is temperature contours with stream lines superimposed.
For more information about the X33, visit the NASA X33 web site at http://x33.msfc.nasa.gov/ .
OAT15A airfoil, hybrid grid. The hybrid grid has 470 points on the airfoil surface, with a total of 29,704 cells (10,824 prisms and 18,880 hexahedra). The viscous layer around the airfoil consists of 40 layers of hexagonal cells extending out approximately 0.05 meters. The far-field boundary extends out 20 chord lengths.The solution was obtained using the Wilcox K-Omega two equation turbulence model.
Surface grid and pressure contours on a F/A-18C. The geometry consists of a F/A-18C aircraft with AIM9 missile and rail, 330 gallon tank mounted below the inboard pylon, and a JDAM/MK-84 mounted below the outboard pylon. The grid consists of 8 zones, with approximately 1.5 million cells. The solution was obtained utilizing 64 SGI R10000 processors, and required approximately 4 1/2 hours to converge five orders.
Symmetry plane grid and surface Mach contours on an F/A-18C.
During the late sixties a series of probes were flown in a velocity regime in which ionization would play an important role. The probes were instrumented to measure electron number densities. The second series of test, known as the Ram-C II experiments, have become a popular test case for modern CFD codes because no ablation products were produced.

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