RFP J.1.(b).9 Technical Library .docx

80ARC023R0006

Attachment J.1.(b).9

FOR INFORMATIONAL PURPOSES ONLY

Publications https://ntrs.nasa.gov/

1. Matsuno, K. V., Childs, R.E., Pulliam, T.H., Stremel P.M., and Garcia, J.A., “OVERFLOW Analysis of Supersonic Retropropulsion Testingon the CobraMRV Mars Entry Vehicle Concept”, AIAA 2022-0913, 2022 SciTech Forum.

2. Denison, M., Garcia, J.A., Nikaido, B.E., Murman, S., Ross, J., Childs, R., Stremel, P., Kleb, W., Alter, S., West, T., Robinson, P., “Evaluation of CFD Predictions of CobraMRV Control Surface Effectiveness at the NASA Langley Unitary Plan Wind Tunnel”, AIAA 2021-2965 2021 Aviation Forum. (Best Paper)

3. Cianciolo, A. D., Korzun, A., Samareh, J., Sostaric, R., Calderon, D., and Garcia, J., “Human Mars Entry, Descent, and Landing Architecture Study Overview.” AIAA SciTech Form 2020, Orlando, FL, AIAA 2020-1509.

4. Calderon, D., Sostaric, R.R., Garcia, J.A., Bowles, J.V., Kinney, D.J., Gaytan, C., Newton, H., Amar, J., and Wiens, Z., “Human Mars Entry, Descent, and Landing Architecture Study: Phase 3 Summary”, AIAA SciTech Form 2020, Orlando, FL, AIAA 2020-1509.

5. Polsgrove, T. T., Percy, T. K., Garcia, J., Cianciolo, A. D. Samareh, J., Lugo, R., Robertson, E., Cerimele, C., Sostaric, R., and Garcia, J., “Human Mars Entry, Descent and Landing Architecture Study: Rigid Decelerators.” AIAA SPACE 2018, Orlando, FL, AIAA 2018-5192.

6. Cerimele, C. J., Robertson, E. A., Sostaric, R. R. (editor), Campbell, C. H., Robinson, P., Matz, D. A., Johnson, B. J., Stachowiak, S. J., Garcia, J. A., Bowles, J. V., Kinney, D. J., Theisinger, J. E. “Entry, Descent, and Landing Performance for a Mid-Lift-to-Drag Ratio Vehicle at Mars” AIAA Paper 2017-1898, Feb 2017.

7. Souza, S.D., Kinney D.J., Garcia J. A., Sarigul-Klijn, N., “Potential for Integrating Entry Guidance into the Multi-Disciplinary Entry Vehicle Optimization Environment”, AIAA Sci Tech Conference 2014.

8. Agrawal, P., Allen, G.A, Hwang H.H., Marley, M.S., McGuire M. K., Garcia J.A., Sklyanskiy, E., Huynh L. C., Moses, R. W., “Atmospheric Entry Studies for Uranus.” IPPW-11, 2014.

9. Sepka, Steven A., Samareh, Jamshid A., “Thermal Protection System Mass Estimating Relationships for Blunt-Body, Earth Entry Spacecraft”, AIAA Thermophysics Conference, 2015.

10. Wright, Michael J., Brandis, Aaron M., Hughes, Monica F., “Technology Development and Infusion by NASA's Entry Systems Modeling Project”, International Conference on Flight Vehicles, Aerothermodynamics and Re-entry Missions & Engineering (FAR), 2019.

11. Mahzari, Milad, White, Todd, “Mars Science Laboratory Heatshield Flight Data Analysis”, Hypersonic Vehicle Flight Prediction Workshop, 2017.

12. Mahzari, Milad, Milos, Frank S., “Sizing and Margin Methodology for Dual-Layer Thermal Protection Systems”, 15th International Planetary Probe Workshop, 2018.

13. Ellerby, Donald T., Gasch, Matthew J., “ Heatshield for Extreme Entry Environment Technology (HEEET) Thermal Protection System (TPS)”, Annual Conference on Composites, Materials, and Structures, 2019.

14. Hwang, Helen H., “A Common Probe Design for Multiple Planetary Destinations”, Outer Planets Assessment Group, 2018.

15. Ellerby, Donald T., Hwang, Helen H., Gasch, Matthew J., Beck, Robin, White, Todd, “TPS and Entry Technologies for Future Outer Planet Exploration”, Planetary Science Decadal Community White Papers, 2020.

16. Hwang, Helen H., “Tales from the Mars Science Laboratory Thermal Protection System Development (or, Try Not to Panic When Your Heatshield Material Disappears)”, Semi-Therm 34, 2018.

17. Brandis, Aaron, et al, “Aerothermodynamics for Dragonfly's Titan Entry”, International Planetary Probe Workshop (IPPW), 2018.

18. Wright, Michael J. et al, “Aerothermal Modeling Challenges for Entry Descent and Landing Missions”, AIAA Aviation, 2018.

19. Stackpoole, Mairead, “TPS Architectures and the Influence of Material and Architecture on Failure Mode Evolution”, Ablation Workshop, 2018.

20. Barnhardt, Michael, et al, “Recent Advancements in Modeling and Simulation of Entry Systems at NASA”, IEEE Aerospace, 2021.

21. Venkatapathy, Ethiraj, et al, “Enabling Future Venus In-situ Missions: Heat-Shield for Extreme Entry Environment Technology (HEEET) Progress towards TRL 6”, Meeting of the Venus Exploration and Analysis Group (VEXAG), 2018.

22. “Hwang, Helen H., et al, “Mars 2020 Entry, Descent and Landing Instrumentation 2 (MEDLI2)”, AIAA Aviation, 2018.

23. Mahzari, Milad, Ellerby, Donald T., Gage, Peter J., “Challenges in Qualification of Thermal Protection Systems for Extreme Entry Environments”, IPPW, 2019.

24. Barnhardt, Michael, et al, “Technology Development and Infusion by NASA's Entry Systems Modeling Project”, International Conference on Flight Vehicles, Aerothermodynamics and Re-entry Missions & Engineering (FAR) 2019.

25. Palmer, Grant, et al, “Modeling Heatshield Erosion Due to Dust Particle Impacts for a Martian Entry Vehicle”, International Conference on Flight Vehicles, Aerothermodynamics and Re-entry Missions & Engineering (FAR) 2019.

26. Venkatapathy, Ethiraj, “Ablators - From Apollo to Future Missions to Moon, Mars and Beyond”, International Astronautical Conference, 2019.

27. Santos, Jose, “Entry, Descent, and Landing Instrumentation”, Planetary Sciences Decadal Survey 2023-2032, 2020.

28. Ellerby, Donald T., “TPS and Entry Technologies for Future Outer Planet Exploration”, Planetary Science Decadal Community White Papers, 2020.

29. Ferguson, Joseph, Semeraro, Federico, “PuMA v3 video tutorials for open-source release”, 2021.

30. Robust and Mass Efficient Thermal Protection Systems for Future Venus Missions”, 2021 Annual Meeting of the Venus Exploration Analysis Group (VEXAG).

31. Stackpoole, Mairead, “”

32. Barnnhardt, Michael, et al, “Modeling Entry Systems to Explore Our Solar System”, Ames Summer Series, 2022.

33. Cummings, Haley, et al, “Overview and Introduction of the Rotor Optimization for the Advancement of Mars eXploration (ROAMX) Project”, Aeromechanics for Advanced Vertical Flight Technical Meeting, Transformative Vertical Flight, 2022

34. Omidy, Ali D., “Code-to-Code Comparison, and Material Response Modeling of Stardust and MSL using PATO and FIAT, 2015.

35. Milos, Frank, Chen, Y.K., “Ablation, Thermal Response, and Chemistry Program for Analysis of Thermal Protection Systems”, 10th AIAA/ASME Joint Thermophysics and Heat Transfer Conference, 2010.

36. Thornton, John, “ ”, Conference on Composites, Materials, and Structures, 2022.

37. Ferguson, Joseph, “Recent Developments to the Porous Microstructure Analysis (PuMA) Software”, Ablation Workshop, 2018.

38. Ferguson, Joseph, “PuMA and Multiscale Modeling”, 45th Annual Conference on Composites, Materials, and Structures”, 2021.

39. Garcia, Joseph, et al, “COBRA (Co-Optimized Bluntbody Re-entry Analysis): A mission optimization process by which an entry system is co-optimized along with its trajectories, thermal protection system, structures, and subsystems to satisfy a set of stakeholder objectives”, 2021.

40. “Predicting Orion Launch Abort Acoustics,” by Cadieux et. al.,ICCFD 2022.

41. “HLPW-4/GMGW-3: Wall-Modeled LES and Lattice-Boltzmann Technology Focus Group Workshop Summary,” by Kiris et. al., AIAA Aviation 2022

42. “A Reynolds-Averaged Navier-Stokes Perspective for the High Lift Common Research Model Using the LAVA Framework,” by Duensing et. al., AIAA AVIATION 2022

43. “A Wall-Modeled LES Perspective for the High Lift Common Research Model Using LAVA,” by Ghate et. al., AIAA AVIATION 2022

44. “A Reynolds-Averaged Navier-Stokes Perspective for the High Lift Common Research Model Using the LAVA Framework,” by Browne et. al., AIAA Aviation 2022

45. “Wall-Modeled Large-Eddy Simulations of Jet Noise in Flight Conditions,” by Stich et. al., 28th AIAA/CEAS Aeroacoustics 2022

46. “Predictions of LAGOON Nose Landing Gear Flow and Noise Using Wall-Modeled Large-Eddy Simulations,” by Wong et. al., 28th AIAA/CEAS Aeroacoustics 2022

47. “High-Lift Common Research Model: RANS, HRLES and WMLES Perspectives for CLmax Prediction Using LAVA,” by Kiris et. al., AIAA SCITECH 2022

48. “Scale-Resolving Simulations of a Supersonic Retro-Propulsion Concept For Mars Entry, Descent, and Landing,” by Cadieux et. al., AIAA SCITECH 2022

49. “Space Launch System Booster Separation Aerodynamic Testing in the NASA Langley Unitary Plan Wind Tunnel,” by Koch et. al., AIAA AVIATION 2021

50. “Transonic Lift and Drag Predictions using Wall Modelled Large Eddy Simulations,” by Ghate et. al., AIAA Scitech 2021

51. “Scale resolving simulations of the NASA Juncture Flow Model using the LAVA solver,” by Ghate et. al., AIAA AVIATION 2020

Software https://ntrs.nasa.gov/

· DPLR

· Data Parallel Line Relaxation Code (DPLR), Version 4(ARC-16021-1A) | NASA Software Catalog

· Introduction to DPLR - NASA Technical Reports Server (NTRS)

· Example Applications:

· Aerothermodynamic Environments Definition for the Mars Science Laboratory Entry Capsule - NASA Technical Reports Server (NTRS)

· MEDLI2: MISP Measured Aftbody Aerothermal Environments - NASA Technical Reports Server (NTRS)

· MEDLI2: MISP Inferred Aerothermal Environment and Flow Transition Assessment - NASA Technical Reports Server (NTRS)

· Computational Investigation of Powered Descent for Human-Scale Mars Landers - NASA Technical Reports Server (NTRS)

· Post-Flight Aerodynamic and Aerothermal Model Validation of a Supersonic Inflatable Aerodynamic Decelerator - NASA Technical Reports Server (NTRS)

· CFD Simulations of the IHF Arc-Jet Flow: 9-Inch Nozzle, Flow Surveys, LEAF Wedge Calibration Data - NASA Technical Reports Server (NTRS)

· NEQAIR

· NEQAIR v15.x, Nonequilibrium Radiative Transport and Spectra Program(ARC-15262-1B) | NASA Software Catalog

· NEQAIR96,Nonequilibrium and Equilibrium Radiative Transport and Spectra Program: User's Manual - NASA Technical Reports Server (NTRS)

· An Essential Radiation Analysis Tool for Space Exploration: NEQAIR v15.1 Tutorial - NASA Technical Reports Server (NTRS)

· Example Applications:

· Coupled Fluids-Radiation Analysis of a High-Mass Mars Entry Vehicle - NASA Technical Reports Server (NTRS)

· Simulations of Hayabusa2 Atmospheric Entry and Comparisons with Data from the Imaging Campaign - NASA Technical Reports Server (NTRS)

· Analysis of Nonequilibrium Molecular Nitrogen Ultraviolet Radiation in Pure N2 Shockwaves - NASA Technical Reports Server (NTRS)

· Radiative Heating in MSL Entry: Comparison of Flight Heating Discrepancy to Ground Test and Predictive Models - NASA Technical Reports Server (NTRS)

· US3D

· UMN Licensing Page: US3D: Aerodynamic and Aerothermodynamic Simulations Software (20110126, Dr. Graham Candler) available from Technology Commercialization (umn.edu)

· Development of the US3D Code for Advanced Compressible and Reacting Flow Simulations - NASA Technical Reports Server (NTRS)

· Dynamic CFD Simulations of the MEADS II Ballistic Range Test Model - NASA Technical Reports Server (NTRS)

· Rapid Hypersonic Simulations using US3D and Pointwise - NASA Technical Reports Server (NTRS)

· Enabling Metric-Based Mesh Adaptation for Advanced Compressible Flow Simulations Using US3D - NASA Technical Reports Server (NTRS)

· Simulation of Dust-Laden Flow in the DLR L2K Facility - NASA Technical Reports Server (NTRS)

Facilities:

· EAST:

· Shock Tube and Ballistic Range Facilities at NASA Ames Research Center - NASA Technical Reports Server (NTRS)

· Recent Progress in Entry Radiation Measurements in the NASA Ames Electric ARC Shock Tube Facility - NASA Technical Reports Server (NTRS)

· Shock Tube Radiation Measurements in Nitrogen - NASA Technical Reports Server (NTRS)

· Shock Radiation Tests for Saturn and Uranus Entry Probes - NASA Technical Reports Server (NTRS)

· Titan Atmospheric Entry Radiative Heating - NASA Technical Reports Server (NTRS)

· HFFAF:

· Design Guide for Aerodynamics Testing of Earth and Planetary Entry Vehicles in a Ballistic Range - NASA Technical Reports Server (NTRS)

· Afterbody Heat Flux Measurements in the NASA Ames HFFAF Ballistic Range - NASA Technical Reports Server (NTRS)

· Upgrades and Modifications of the NASA Ames HFFAF Ballistic Range - NASA Technical Reports Server (NTRS)

· Aerodynamic Coefficients from Aeroballistic Range Testing of Deployed- and Stowed-SIAD SFDT Models - NASA Technical Reports Server (NTRS)

· Rough-Wall Turbulent Heat Transfer Experiments in Hypersonic Free Flight - NASA Technical Reports Server (NTRS)

· Transition Experiments on Blunt Bodies with Distributed Roughness in Hypersonic Free Flight in Carbon Dioxide - NASA Technical Reports Server (NTRS)

NASA Software Catalog https://software.nasa.gov/

ARC-15779-1A

Fully Implicit Ablation and Thermal Analysis Program, Version 3 (FIAT v3) - unrestricted version FIAT v3 simulates one-dimensional thermal energy transport in a multilayer stack of isotropic materials and structures that can ablate from the front surface and decompose in depth. The implicit solution algorithm and general solution technique make the program very stable and robust for application to both robotic and crewed vehicles entering a planetary atmosphere from space. For input, the code reads material property information from a database file.

U.S. and Foreign Release

ARC-15016-1A

TPSSizer (aka TPSSZR) - Vehicle TPS sizing program using FIAT TPSSizer is a Thermal Protection System (TPS) sizing tool developed at ARC for use in conceptual level through detailed design level analysis. TPS sizing methodologies and data exchange interfaces with supporting disciplines were developed for TPSSizer. Additionally, the tool introduced improvement to prior art with the automatic generation of TPS stackups, automatic generation of aerothermal environment files, maintenance of consistent material properties descriptions, the capability to simultaneously evaluate multiple nominal and abort flight trajectories and the development of methodologies for the application of appropriate design margins.

U.S. and Foreign Release

ARC-16680-1A

Porous material Analysis Toolbox based on OpenFoam (PATO) The Porous material Analysis Toolbox (PATO) is a modular analysis platform for multiphase porous reactive materials. It can be run as a simple Fourier heat transfer code or include more advanced features as internal decomposition (pyrolysis, vaporization), gas-gas and gas-solid chemical interactions (combustion, cracking, coking), gas species transport (convection, diffusion), and solid morphology evolutions (internal density changes, surface ablation). PATO is implemented as a C top level module of the open source (GNU GPL) computational fluid dynamics software program OpenFOAM. This offering is not approved or endorsed by OpenCFD Limited, the producer of the OpenFOAM software and owner of the OPENFOAM and OpenCFD trademarks. PATO also uses the open source (GNU LGPL) thermodynamics, transport, and chemistry library Mutation produced by the von Karman Institute for Fluid Dynamics.

Open Source

ARC-17920-1A

Porous Microstructure Analysis (PuMA) The Porous Microstructure Analysis (PuMA) software has been developed in order to compute effective material properties and perform material response simulations on digitized microstructures of porous media. PuMA is able to import digital three-dimensional images obtained from X-ray microtomography or to generate artificial microstructures that mimic real materials. PuMA also provides a module for interactive 3D visualizations. Version 3 includes modules to compute simple morphological properties such as porosity, volume fractions, pore diameter, and specific surface area. Additional capabilities include the determination of effective thermal and electrical conductivity (including the ability to simulate local anisotropy), effective diffusivity and tortuosity from the continuum to the rarefied regime, and techniques to determine local material orientation.

Open Source

ARC-16021-1A

Data Parallel Line Relaxation Code (DPLR), Version 4 The DPLR software package is a suite of CFD tools for the computation of supersonic and hypersonic flows in chemical and thermal nonequilibrium. Included in the package are 2D/axisymmetric and 3D structured grid finite volume Navier-Stokes codes, a pre-processor, and a post-processor. The code supports implicit boundary conditions, generalized multi-block topologies, grid alignment to flow features, and generalized chemical kinetics and thermodynamic property databases.

U.S. Government Purpose Release

ARC-15262-1B

NEQAIR v15.x, Nonequilibrium Radiative Transport and Spectra Program NEQAIR is NASAs most long standing radiative heating code for flight predictions and simulating experiments. It is a line-by-line radiation code that computes spontaneous emission, absorption and stimulated emission due to transitions between various energy states of chemical species along a line-of-sight through a non-uniform gas mixture. This allows NEQAIR to calculate the radiative heat flux and detailed spectra at a specified location. NEQAIR v15.1 has focused on improving physics, solution robustness for 3D and coupled calculations, and providing more control for running the code.

U.S. and Foreign Release

ARC-15117-1A

Pegasus 5.2: Software For Automated Pre-Processing of Overset CFD Grids The Pegasus software is used as a pre-processor for overset-grid Computational Fluid Dynamics (CFD) simulations. It provides the hole-cutting and connectivity information between structured overset grids. The main features of the software include automated hole-cutting algorithms, a projection scheme for fixing small discretization errors in overset surface; efficient interpolation search methods; hole-size optimization based on adding additional layers of fringe points; and an automatic restart capability. The code can run in parallel using the Message-Passing Interface (MPI) standard. The parallel performance provides efficient speed-up of the execution time utilizing dozens or even hundreds of processors. The additional capabilities in the new 5.2 version include: support for cell-centered grids; triple-fringe option; automated domain decomposition into multiple hole-cutters; improved parallel execution load-balancing algorithm; and additional minor enhancements.

U.S. Release Only

LAR-20095-1

OVERFLOW 2.4 Overset Grid Computational Fluid Dynamics Flow Solver with Moving Body Capability (OVERFLOW) OVERFLOW 2.4 is a computer code for simulating viscous, compressible fluid flow about complex aerodynamic configurations. The technology solves the Reynolds-averaged Navier-Stokes equations using structured, overset computational grids. It includes the capability for simulating multiple moving bodies acting under prescribed or aerodynamically forced motion. OVERFLOW 2 is a merge of the previously developed OVERFLOW 1.8 and OVERFLOW-D codes.

U.S. Release Only

ARC-15601-1

Finite-Rate Chemistry, Overset-Grid, Dual-Time Combustion-Reentry Code This technology modifies the OVERFLOW code for finite rate and equilibrium chemistry by substituting the perfect gas model built into the code with a model assuming a gas made up of a mixture of thermally perfect gases. Four extra field variables were added, corresponding to pressure, temperature, coefficient of thermal conductivity, and the new pressure derivative X.

NASA Ames Research Center Websites:

https://www.nasa.gov/ames/aeronautics/systems-analysis-office https://www.nasa.gov/ames/aeronautics/projects https://rotorcraft.arc.nasa.gov/ https://www.nasa.gov/centers/ames/entry-systems-and-technology https://www.nasa.gov/centers/ames/aerothermodynamics/index.html https://www.nasa.gov/centers/ames/thermal-protection-materials/index.html https://www.nasa.gov/centers/ames/entry-systems-vehicle-development/index.html

Seminar Series:

Advanced Modeling & Simulation (AMS) Seminar Series - https://www.nas.nasa.gov/pubs/ams.html

EDL Summer Seminar Series - https://nescacademy.nasa.gov/playlist/93370fbf5202434d9a77e02f1285d98254

Note: The information contained with the technical library (Attachment J.1.(b).9) is provided for informational purposes and the government does not assert to the accuracy or validity of the data and its use in the development of an Offeror’s response to proposal requirements stated in Section L of this RFP.