This Gallery page exists to show interesting visual images
created in the Caselab.
The shock tube is a classic testcase for CFD verification.
Our unstructured finite element codes generate a sparse symmetric connectivity influence matrix called the mass matrix. Allthough the matrix for a typical problem is huge, (N,N) with N in the millions, each row only has on the order of 2 to 10 non-zero terms. Naturally, the matrix is neither calculated nor stored. Rather, the multiplication of the matrix with a vector is defined: V=M*a. The images below show a small geometry and a particular mass matrix resulting from that geometry.
This hypersonic geometry serves as a combustion prototyping and research testbed. Flight conditions are Mach 10.5. Mach (left), Combustor Pressure (center), and Vehicle Pressure (right) are shown for combustion off (top) and on (bottom). The thrust matches drag by throttling the combustion rate.
This F-18 geometry is a classic testcase in our lab for whole-aircraft simulations and experiments.
OSU Black 2007
The 2007 OSU Black team requested the Caselab conduct CFD analysis of their aircraft prototype. More information is at OSU Aerodesign
Navier Stokes Separated Flow:
Our Navier Stokes solver allows us to simulate separated flows.
Rigid Body Flight Dynamics
Coupling our non-inertial CFD solver with a quaternion attitute representation allows us to simulate non-linear flight dynamics. The following experiment shows the flight dynamics of a North American Navion. The two loop cases illustrate the flight dynamics of forward and aft CG locations.
NASA Ares (Mars Plane)
An undergraduate summer intern, Josh Coltrane, modeled the NASA Ares aircraft from scratch. The geometry data came from published literature and photos, so we were pleased with his reverse-engineered results. Using CFD derived aerodynamic data, he modeled an atmospheric entry onto Mars.
The fin image comes from Tony Buratti's dragster thesis. Other images are from various projects and experiments.
Computational grids are a critical part of CFD. This is a sample of some simple and complex surface grids. In general, the grid resolution depends on the solution type and an acceptable solution error.
OSU Black 2002
The 2002 DBF black team requested that the Caselab conduct CFD analysis of their aircraft prototype. Our conclusions predicted the aircraft's unusual pitch-axis behaviour, which was clearly evident during multiple test-flights. Adding pitch feedback via a gyro solved the S&C problem. More information is at OSU Aerodesign: Falcon.
Wing: NACA 0009
The NACA 0009 is a classic testcase for validation. Comparing the top left and top center images shows the fundamental difference between subsonic and supersonic flow.
UPDATE: We regenerated the streamline image based on a request.
Shocks and fans occur in compressible flow. The following shock occurs a wedge angle of 15 degrees and Mach 2.5.