NASA_Software_Catalog_2014.pdf#sthash.Rk7M8wlL

ACD Aerodynamic Design of Multistage Axial-Flow CompressorsLEW-17448ACD is an analysis code used for the aerodynamic design of multistage axial-flow compressors. The technologyprovides velocity diagrams on the streamlines at the blade-row edges. Blade elements are definedby centerline curve and thickness distribution, and blade-element inlet and outlet angles are establishedthrough empirical incidence and deviation-angle adjustments to the velocity diagrams. Blade elements canbe stacked to provide the full blade design.U.S. Release OnlyACOD Multistage Axial-Flow Compressor Off-designLEW-17449A companion tool to Glenn Research Center’s ACD software (LEW-17448), ACOD is streamline analysis codefor predicting the off-design performance of multistage axial-flow compressors. Flow, blading, and loss aremodeled similarly to ACD.U.S. Release OnlyAdvanced Ducted Propfan Analysis Code (ADPAC)LEW-16768Note: Software Restricted by Export ControlDeveloped by the Allison Engine Company under contracts with Glenn Research Center, ADPAC solvestightly coupled internal/external flows through future-concept short-duct turbofan engines.U.S. Release OnlyAxial-Flow Turbine Off-Design (AXOD) PerformanceLEW-16323AXOD computes the flow and efficiency of multistage axial-flow turbines as functions of speed and pressureratio. The technology uses a span-line analysis with simple radial equilibrium. The loss model includesblade-row inlet losses, blade-row losses, and stage-test losses. Coefficients are selected to match theknown design-point performance, and the internal model provides the off-design performance.U.S. Release OnlyBLAYERLEW-P44BLAYER is a Fortran program used for calculating compressible laminar and turbulent boundary layers inarbitrary pressure gradients.U.S. Release OnlyBoundary-Layer Matrix Procedure Kinetic (BLIMPK) Modernization and UpgradeMSC-25641-1Written in Fortran, BLIMPK solves boundary-layer equations for arbitrary chemically reacting gases. NASA,the Department of Defense, and industry have all used the software in the design and evaluation of rocketnozzles and reentry spacecraft.U.S. Government Purpose ReleaseBroadband Fan Noise Prediction System (BFaNS)LEW-17307BFaNS computes the broadband noise generated by a turbofan engine’s fan stage. Noise sources caninclude turbulence impingement and boundary-layer turbulence convection.U.S. Release Only5. PropulsionCentrifugal Off-Design Performance (CCODP) CompressorLEW-17450CCODP is a one-dimensional off-design performance prediction code used for centrifugal compressors.Correlations account for the following types of loss: inlet guide vane, impeller incidence, shock, skin friction,blade loading, trailing edge, clearance, vaneless and vaned diffuser friction, recirculation, and disk friction.U.S. Release Only42NASA Technology Transfer Program Software Catalog 2014