Scientific Simulations, Llc
CAGE Code: 4JAH3
NCAGE Code: 4JAH3
Status: Active
Type: Commercial Supplier
Dun & Bradstreet (DUNS): 831107271
Summary
Scientific Simulations, Llc is an Active Commercial Supplier with the Cage Code 4JAH3 and is tracked by Dun & Bradstreet under DUNS Number 831107271..
Address
2100 Bear Dr
Steamboat Springs CO 80487-2079
United States
Points of Contact
No Points of Contact...
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Frequently Asked Questions (FAQ) for CAGE 4JAH3
- What is CAGE Code 4JAH3?
- 4JAH3 is the unique identifier used by NATO Organizations to reference the physical entity known as Scientific Simulations, Llc located at 2100 Bear Dr, Steamboat Springs CO 80487-2079, United States.
- Who is CAGE Code 4JAH3?
- 4JAH3 refers to Scientific Simulations, Llc located at 2100 Bear Dr, Steamboat Springs CO 80487-2079, United States.
- Where is CAGE Code 4JAH3 Located?
- CAGE Code 4JAH3 is located in Steamboat Springs, CO, USA.
Contracting History for CAGE 4JAH3 Most Recent 25 Records
- 80NSSC23PB565
- Fy23 Sbir Phase I - Dynamic Adaptive Mesh Refinement For Wall Modeled Les Of Complex Configurations
- 20 Jul 2023
- Fy23 Sbir Phase I - Dynamic Adaptive Mesh Refinement For Wall Modeled Les Of Complex Configurations
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $155,316.00
- National Aeronautics And Space Administration (Nasa)
- 80NSSC22PB178
- E014042 Sbir Phase I Scientific Simulations, Llc
- 23 Jul 2022
- E014042 Sbir Phase I Scientific Simulations, Llc
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $155,482.00
- National Aeronautics And Space Administration (Nasa)
- 80NSSC19C0090
- Optimization Of Supersonic Jet Noise Using A Reynolds-Averaged Navier-Stokes Approach
- 10 Nov 2020
- Optimization Of Supersonic Jet Noise Using A Reynolds-Averaged Navier-Stokes Approach
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $748,466.00
- National Aeronautics And Space Administration (Nasa)
- 80NSSC19C0090
- Optimization Of Supersonic Jet Noise Using A Reynolds-Averaged Navier-Stokes Approach
- 5 Mar 2021
- Optimization Of Supersonic Jet Noise Using A Reynolds-Averaged Navier-Stokes Approach
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $748,466.00
- National Aeronautics And Space Administration (Nasa)
- 80NSSC19C0090
- Optimization Of Supersonic Jet Noise Using A Reynolds-Averaged Navier-Stokes Approach
- 13 Aug 2019
- Optimization Of Supersonic Jet Noise Using A Reynolds-Averaged Navier-Stokes Approach
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $748,466.00
- National Aeronautics And Space Administration (Nasa)
- 80NSSC21C0209
- The Objective Of This Phase 1 Proposal Is The Graphical-Processing-Unit (Gpu) Acceleration Of A Two-Dimensional,.Unstructured, Viscous Navier-Stokes (Ns) Solver For Aerothermodynamic Applications.
- 8 Sep 2021
- The Objective Of This Phase 1 Proposal Is The Graphical-Processing-Unit (Gpu) Acceleration Of A Two-Dimensional,.Unstructured, Viscous Navier-Stokes (Ns) Solver For Aerothermodynamic Applications.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $124,950.00
- National Aeronautics And Space Administration (Nasa)
- 80NSSC21C0209
- The Objective Of This Phase 1 Proposal Is The Graphical-Processing-Unit (Gpu) Acceleration Of A Two-Dimensional,.Unstructured, Viscous Navier-Stokes (Ns) Solver For Aerothermodynamic Applications.
- 3 Mar 2022
- The Objective Of This Phase 1 Proposal Is The Graphical-Processing-Unit (Gpu) Acceleration Of A Two-Dimensional,.Unstructured, Viscous Navier-Stokes (Ns) Solver For Aerothermodynamic Applications.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $124,950.00
- National Aeronautics And Space Administration (Nasa)
- 80NSSC18P1888
- The Objective Of This Proposal Is The Development And Demonstration Of A Cost-Effective High-Fidelity Aeroacoustic Design Tool For Future Commercial Supersonic Nozzle Designs And Installations. Although Eddy-Resolving Cfd Methods For Computing High-Speed Jet Noise Are Available, Such Methods Are Computationally Expensive And Are Currently Deemed Impractical For Use In A Design Optimization Loop. On The Other Hand, The Prediction Of Turbulence Generated Noise Using The Rans Equations Provides A Less Accurate But More Cost-Effective Approach For Practical Design Problems, Wherein The Turbulence Length And Time Scales Needed To Model The Local Noise Source Terms Can Be Extracted From The Rans Turbulence Model Solution, As Performed By The Nasa Jeno Code. In This Phase 1 Proposal, We Seek To Demonstrate The Feasibility Of Using The Exact Discrete Adjoint Of A Coupled Rans-Jeno Turbulent Noise Prediction Methodology For Optimizing Far-Field Acoustic Objectives Of Jet Noise. Based On Our Previous Experience Developing An Unsteady Rans-Fwh (Ffowcs Williams-Hawkings) Far-Field Acoustic Optimization Capability, The Phase 1 Proposal Targets The Formulation Of The Turbulence Noise Source Terms Used By The Jeno Code, Along With The Discrete Adjoint Of These Terms Within An Existing Adjoint-Enabled Rans Solver. The Immediate Goal Will Be To Demonstrate The Possibility Of Reducing These Noise Sources Through Nozzle Shape Optimization. In Phase 2, This Capability Will Be Linked With The Nasa Jeno Code, And The Remaining Terms For The Formulation Of The Discrete Adjoint Of The Coupled Rans-Jeno Simulation Capability Will Be Implemented And Used To Perform Optimization Of Far-Field Noise Signatures For Realistic Nozzle Configurations. By Targeting The Specific Terms That Drive The Noise Propagation In The Jeno Formulation, Our Phase 1 Approach Will Demonstrate The Feasibility Of Using A Fully Coupled Rans-Jeno Code For Cost-Effective Gradient-Based Jet Noise Optimization.
- 12 Feb 2019
- The Objective Of This Proposal Is The Development And Demonstration Of A Cost-Effective High-Fidelity Aeroacoustic Design Tool For Future Commercial Supersonic Nozzle Designs And Installations. Although Eddy-Resolving Cfd Methods For Computing High-Speed Jet Noise Are Available, Such Methods Are Computationally Expensive And Are Currently Deemed Impractical For Use In A Design Optimization Loop. On The Other Hand, The Prediction Of Turbulence Generated Noise Using The Rans Equations Provides A Less Accurate But More Cost-Effective Approach For Practical Design Problems, Wherein The Turbulence Length And Time Scales Needed To Model The Local Noise Source Terms Can Be Extracted From The Rans Turbulence Model Solution, As Performed By The Nasa Jeno Code. In This Phase 1 Proposal, We Seek To Demonstrate The Feasibility Of Using The Exact Discrete Adjoint Of A Coupled Rans-Jeno Turbulent Noise Prediction Methodology For Optimizing Far-Field Acoustic Objectives Of Jet Noise. Based On Our Previous Experience Developing An Unsteady Rans-Fwh (Ffowcs Williams-Hawkings) Far-Field Acoustic Optimization Capability, The Phase 1 Proposal Targets The Formulation Of The Turbulence Noise Source Terms Used By The Jeno Code, Along With The Discrete Adjoint Of These Terms Within An Existing Adjoint-Enabled Rans Solver. The Immediate Goal Will Be To Demonstrate The Possibility Of Reducing These Noise Sources Through Nozzle Shape Optimization. In Phase 2, This Capability Will Be Linked With The Nasa Jeno Code, And The Remaining Terms For The Formulation Of The Discrete Adjoint Of The Coupled Rans-Jeno Simulation Capability Will Be Implemented And Used To Perform Optimization Of Far-Field Noise Signatures For Realistic Nozzle Configurations. By Targeting The Specific Terms That Drive The Noise Propagation In The Jeno Formulation, Our Phase 1 Approach Will Demonstrate The Feasibility Of Using A Fully Coupled Rans-Jeno Code For Cost-Effective Gradient-Based Jet Noise Optimization.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $121,067.00
- National Aeronautics And Space Administration (Nasa)
- 80NSSC20C0380
- Unstructured Overset Hybrid Rans/Les Simulations For Jet Noise Prediction
- 11 Feb 2021
- Unstructured Overset Hybrid Rans/Les Simulations For Jet Noise Prediction
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $118,105.00
- National Aeronautics And Space Administration (Nasa)
- 80NSSC18P1888
- The Objective Of This Proposal Is The Development And Demonstration Of A Cost-Effective High-Fidelity Aeroacoustic Design Tool For Future Commercial Supersonic Nozzle Designs And Installations. Although Eddy-Resolving Cfd Methods For Computing High-Speed Jet Noise Are Available, Such Methods Are Computationally Expensive And Are Currently Deemed Impractical For Use In A Design Optimization Loop. On The Other Hand, The Prediction Of Turbulence Generated Noise Using The Rans Equations Provides A Less Accurate But More Cost-Effective Approach For Practical Design Problems, Wherein The Turbulence Length And Time Scales Needed To Model The Local Noise Source Terms Can Be Extracted From The Rans Turbulence Model Solution, As Performed By The Nasa Jeno Code. In This Phase 1 Proposal, We Seek To Demonstrate The Feasibility Of Using The Exact Discrete Adjoint Of A Coupled Rans-Jeno Turbulent Noise Prediction Methodology For Optimizing Far-Field Acoustic Objectives Of Jet Noise. Based On Our Previous Experience Developing An Unsteady Rans-Fwh (Ffowcs Williams-Hawkings) Far-Field Acoustic Optimization Capability, The Phase 1 Proposal Targets The Formulation Of The Turbulence Noise Source Terms Used By The Jeno Code, Along With The Discrete Adjoint Of These Terms Within An Existing Adjoint-Enabled Rans Solver. The Immediate Goal Will Be To Demonstrate The Possibility Of Reducing These Noise Sources Through Nozzle Shape Optimization. In Phase 2, This Capability Will Be Linked With The Nasa Jeno Code, And The Remaining Terms For The Formulation Of The Discrete Adjoint Of The Coupled Rans-Jeno Simulation Capability Will Be Implemented And Used To Perform Optimization Of Far-Field Noise Signatures For Realistic Nozzle Configurations. By Targeting The Specific Terms That Drive The Noise Propagation In The Jeno Formulation, Our Phase 1 Approach Will Demonstrate The Feasibility Of Using A Fully Coupled Rans-Jeno Code For Cost-Effective Gradient-Based Jet Noise Optimization.
- 24 Jul 2018
- The Objective Of This Proposal Is The Development And Demonstration Of A Cost-Effective High-Fidelity Aeroacoustic Design Tool For Future Commercial Supersonic Nozzle Designs And Installations. Although Eddy-Resolving Cfd Methods For Computing High-Speed Jet Noise Are Available, Such Methods Are Computationally Expensive And Are Currently Deemed Impractical For Use In A Design Optimization Loop. On The Other Hand, The Prediction Of Turbulence Generated Noise Using The Rans Equations Provides A Less Accurate But More Cost-Effective Approach For Practical Design Problems, Wherein The Turbulence Length And Time Scales Needed To Model The Local Noise Source Terms Can Be Extracted From The Rans Turbulence Model Solution, As Performed By The Nasa Jeno Code. In This Phase 1 Proposal, We Seek To Demonstrate The Feasibility Of Using The Exact Discrete Adjoint Of A Coupled Rans-Jeno Turbulent Noise Prediction Methodology For Optimizing Far-Field Acoustic Objectives Of Jet Noise. Based On Our Previous Experience Developing An Unsteady Rans-Fwh (Ffowcs Williams-Hawkings) Far-Field Acoustic Optimization Capability, The Phase 1 Proposal Targets The Formulation Of The Turbulence Noise Source Terms Used By The Jeno Code, Along With The Discrete Adjoint Of These Terms Within An Existing Adjoint-Enabled Rans Solver. The Immediate Goal Will Be To Demonstrate The Possibility Of Reducing These Noise Sources Through Nozzle Shape Optimization. In Phase 2, This Capability Will Be Linked With The Nasa Jeno Code, And The Remaining Terms For The Formulation Of The Discrete Adjoint Of The Coupled Rans-Jeno Simulation Capability Will Be Implemented And Used To Perform Optimization Of Far-Field Noise Signatures For Realistic Nozzle Configurations. By Targeting The Specific Terms That Drive The Noise Propagation In The Jeno Formulation, Our Phase 1 Approach Will Demonstrate The Feasibility Of Using A Fully Coupled Rans-Jeno Code For Cost-Effective Gradient-Based Jet Noise Optimization.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $121,067.00
- National Aeronautics And Space Administration (Nasa)
- 80NSSC20C0380
- Unstructured Overset Hybrid Rans/Les Simulations For Jet Noise Prediction
- 3 Aug 2020
- Unstructured Overset Hybrid Rans/Les Simulations For Jet Noise Prediction
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $118,105.00
- National Aeronautics And Space Administration (Nasa)
- 80NSSC20C0380
- Unstructured Overset Hybrid Rans/Les Simulations For Jet Noise Prediction
- 14 Oct 2020
- Unstructured Overset Hybrid Rans/Les Simulations For Jet Noise Prediction
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $118,105.00
- National Aeronautics And Space Administration (Nasa)
- 80NSSC21C0209
- The Objective Of This Phase 1 Proposal Is The Graphical-Processing-Unit (Gpu)
- 11 May 2021
- The Objective Of This Phase 1 Proposal Is The Graphical-Processing-Unit (Gpu)
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $124,950.00
- National Aeronautics And Space Administration (Nasa)