Wind-US

Overview
Wind-US may be used to solve various sets of equations governing physical phenomena related to fluid flow. Currently, the code supports the solution of the Euler and Navier-Stokes equations of fluid mechanics using multi-zone structured, unstructured, or hybrid grids, along with additional equation sets governing turbulent and chemically reacting flows.

Swift v. 300

Overview
Swift is a multiblock CFD code for the analysis of 3-D flows in turbomachinery, developed by Dr. Rodrick V. Chima at NASA Glenn Research Center. The code solves the thin-layer Navier-Stokes equations using explicit finite-difference techniques. It can be used to analyze linear cascades or annular blade rows with or without rotation. Limited multiblock capability can be used to model tip-clearances and multistage machines.

LERCINLT

Overview
LERCINLT is a method of characteristics design code for inlets.

INLETMOC

Overview
INLETMOC is a method of characteristics analysis code for inlets.

IPAC

Overview
IPAC is a code that calculates inlet overall performance by using one-dimensional analytical techniques.

PINDAP

Overview
The Planar Inlet Design and Analysis Process (PINDAP) is a collection of software tools that allow the efficient aerodynamic design and analysis of planar (two-dimensional and axisymmetric) inlets. The aerodynamic analysis is performed using the Wind-US computational fluid dynamics (CFD) program. A major element in PINDAP is a Fortran 90 code named PINDAP that can establish the parametric design of the inlet and efficiently model the geometry and generate the grid for CFD analysis with design changes to those parameters.

Rao Code

Overview
The Rao code is an optimum nozzle design code.

MOC/STT Nozzle Design Codes

Overview
MOC/STT is a method of characteristics design tool for nozzles.

LES Code

Overview
A large-eddy simulation (LES) code has been developed within the Inlet and Nozzle Branch to provide more accurate and detailed computational analyses of propulsion flow fields. The LES code is being used to both analyze propulsion system components and test improved LES algorithms (numerical schemes, filters and sub-grid models). The code can utilize a variety of explicit optimized finite difference schemes (stencil sizes up to 13 points) to solve the compressible Favre-filtered Navier-Stokes equations. A compressible form of Smagorinsky's model is used for the subgrid-scale turbulence. The code uses generalized curvilinear coordinates to allow analysis of a wide range of geometries. It is written in Fortran 90 using the Message Passing Interface (MPI) libraries and can been run on a wide variety of parallel computing systems.

JeNo

Overview
The JeNo jet noise prediction code calculates the far-field sound spectral density produced by axisymmetric jets at a user specified observer location and frequency range.