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SNAP is an N-body high-fidelity propagation program that can model the trajectories of the planets, the Sun, and virtually any natural satellite in the solar system.

MAPSS is a flexible turbofan engine simulation environment that provides easy access to health, control, and engine parameters through a graphical user interface. The technology can be used as a simulation environment for developing and testing advanced control algorithms, or it can run transient simulations or generate state-space linear models for creating a piecewise linear controller.

Written in a combination of MATLAB and Simulink, C-MAPSS provides a realistic simulation of a large commercial turbofan engine. The technology includes a number of graphical user-interface screens that allow point-and-click operation.

The V072 computer code predicts noise from rotor wake/stator interactions. The technology can perform compressor rotor wake prediction only, rotor/stator or fan/FEGV interaction only, fan/core stator interaction only, and both fan/FEGV and fan/core stator interactions.

This computer program computes general two-dimensional turbulent boundary-layer flow using finite difference techniques. Without requiring any modifications to the program code, STAN 5 can handle a wide range of boundary-layer problems. The technology has been used extensively at Stanford University.

CT-CURS is a dedicated unwrapping/re-slicing software tool for computing tomography data from cylindrical and partially cylindrical structures. The technology can be used as a complement to vendor software or can be utilized as a completely standalone visualization program.

This technology computes the tone noise associated with propellers and predicts axial and circumferential directivity. The acoustic model is exact and accounts for all unsteady sources.

BLAYER is a Fortran program used for calculating compressible laminar and turbulent boundary layers in arbitrary pressure gradients.

APNASA simulates the three-dimensional viscous flowfield through an entire compressor or turbine consisting of multiple rows of blades in a single computational job. A grid is generated which encompasses all blade rows. Boundary conditions are imposed upstream of the first blade row and downstream of the last blade row-no boundary conditions are set between blade rows. The code marches forward in time on the flowfield solution within all the blade rows. During the solution process the code periodically calculates the time-average glow in each of the blade rows and information required to model blade-row interaction effects between each blade row and its neighbors. The code passes this information to all of the blade rows as it continues forward in time. When the solution converges to a user-specified tolerance, the simulation of the flowfield through the entire turbomachine is realized and the user obtains a time-average description of the three-dimensional viscous flow in each blade row. Since information on blade row interactions is passed from row-to-row throughout the solution process, the simulation includes the time-average effects of neighboring blade rows on one another