Parametric Analysis of Hypersonic Microcavity Arrays - Computational Suite v2.2.1
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2026
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| _version_ | 1866902340066344960 |
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| author | Okushigue, Jefferson M. |
| author_facet | Okushigue, Jefferson M. |
| contents | <pre># HYPERSONIC MICROCAVITY RESEARCH SUITE v2.2.1 ## Overview This Python computational suite performs parametric analysis of discrete hypersonic microcavity arrays for boundary-layer instability damping and thermal protection system (TPS) mass reduction. The code implements validated models for trajectory simulation, aerothermal environment modeling, boundary-layer stability analysis, Helmholtz resonator acoustics, and TPS mass estimation. ## Key Features - **Multi-Vehicle Support**: Artemis, Starship, Apollo, and Space Shuttle configurations - **Realistic Trajectory Profiles**: Based on flight data and telemetry (including IFT-5/IFT-6 data for Starship) - **Parametric Optimization**: Automatic cavity geometry optimization for maximum damping efficiency - **Scalability Analysis**: Linear regression models for mass savings prediction - **Sensitivity Studies**: Multi-parameter sensitivity analysis for design robustness - **Historical Validation**: Cross-vehicle comparison with documented flight data - **Publication-Ready Outputs**: High-quality plots and data export (CSV/JSON) ## Version 2.2.1 Updates - **Fixed**: TPS mass calculation with η-dependent heat load reduction - **Added**: Scalability analysis with efficiency-normalized linear regression - **Updated**: SciPy 1.12+ compatibility and improved numerical stability - **Enhanced**: Realistic trajectory models for all vehicle classes - **Improved**: Data export capabilities and visualization quality ## Applications - Thermal protection system design optimization - Hypersonic boundary-layer transition control - Reusable launch vehicle mass reduction studies - Educational and research use in aerodynamics and aerospace engineering ## Associated Publication This code implements the methodology described in: "Parametric Analysis of Hypersonic Microcavity Arrays for Thermal Protection System Mass Reduction" by Jefferson M. Okushigue (February 2026). ## Technical Details - **Language**: Python 3.10+ - **Dependencies**: NumPy, SciPy, Matplotlib - **License**: MIT - **DOI**: https://doi.org/10.5281/zenodo.18449674 ## Author Jefferson M. Okushigue Independent Researcher ORCID: https://orcid.org/0009-0001-5576-605X Email: okushigue@gmail.com</pre> |
| format | Recurso digital |
| id | zenodo_https___doi_org_10_5281_zenodo_18449674 |
| institution | Zenodo |
| language | |
| publishDate | 2026 |
| publisher | Zenodo |
| record_format | zenodo |
| spellingShingle | Parametric Analysis of Hypersonic Microcavity Arrays - Computational Suite v2.2.1 Okushigue, Jefferson M. "hypersonic flow", "boundary-layer transition", "thermal protection systems", "Helmholtz resonators", "passive flow control", "mass optimization", "reentry vehicles", "computational aerodynamics", "Python", "open source" <pre># HYPERSONIC MICROCAVITY RESEARCH SUITE v2.2.1 ## Overview This Python computational suite performs parametric analysis of discrete hypersonic microcavity arrays for boundary-layer instability damping and thermal protection system (TPS) mass reduction. The code implements validated models for trajectory simulation, aerothermal environment modeling, boundary-layer stability analysis, Helmholtz resonator acoustics, and TPS mass estimation. ## Key Features - **Multi-Vehicle Support**: Artemis, Starship, Apollo, and Space Shuttle configurations - **Realistic Trajectory Profiles**: Based on flight data and telemetry (including IFT-5/IFT-6 data for Starship) - **Parametric Optimization**: Automatic cavity geometry optimization for maximum damping efficiency - **Scalability Analysis**: Linear regression models for mass savings prediction - **Sensitivity Studies**: Multi-parameter sensitivity analysis for design robustness - **Historical Validation**: Cross-vehicle comparison with documented flight data - **Publication-Ready Outputs**: High-quality plots and data export (CSV/JSON) ## Version 2.2.1 Updates - **Fixed**: TPS mass calculation with η-dependent heat load reduction - **Added**: Scalability analysis with efficiency-normalized linear regression - **Updated**: SciPy 1.12+ compatibility and improved numerical stability - **Enhanced**: Realistic trajectory models for all vehicle classes - **Improved**: Data export capabilities and visualization quality ## Applications - Thermal protection system design optimization - Hypersonic boundary-layer transition control - Reusable launch vehicle mass reduction studies - Educational and research use in aerodynamics and aerospace engineering ## Associated Publication This code implements the methodology described in: "Parametric Analysis of Hypersonic Microcavity Arrays for Thermal Protection System Mass Reduction" by Jefferson M. Okushigue (February 2026). ## Technical Details - **Language**: Python 3.10+ - **Dependencies**: NumPy, SciPy, Matplotlib - **License**: MIT - **DOI**: https://doi.org/10.5281/zenodo.18449674 ## Author Jefferson M. Okushigue Independent Researcher ORCID: https://orcid.org/0009-0001-5576-605X Email: okushigue@gmail.com</pre> |
| title | Parametric Analysis of Hypersonic Microcavity Arrays - Computational Suite v2.2.1 |
| topic | "hypersonic flow", "boundary-layer transition", "thermal protection systems", "Helmholtz resonators", "passive flow control", "mass optimization", "reentry vehicles", "computational aerodynamics", "Python", "open source" |
| url | https://doi.org/10.5281/zenodo.18449674 |