Wavefront distortion due to the shock wave and boundary layer in the supersonic flow over a compression ramp
Optical devices equipped in supersonic flight vehicles are subjected to distortions of optical paths due to aero-optical effects, potentially resulting in the degradation of sensing and imaging performance. In this study, the aero-optical effects of the supersonic flow over a two-dimensional compres...
Ausführliche Beschreibung
Gespeichert in:
| Autor*in: |
Lee, Sangyoon [verfasserIn] |
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| Format: |
E-Artikel |
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| Sprache: |
Englisch |
| Erschienen: |
2021transfer abstract |
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| Schlagwörter: |
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| Übergeordnetes Werk: |
Enthalten in: Mo1474 The Role of EUS Examination and EUS-Guided Fine Needle Aspiration Biopsy for Evaluation of Gastric Subepithelial Lesions: a Large Single Center Experience - Baysal, Birol ELSEVIER, 2015, Amsterdam [u.a.] |
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| Übergeordnetes Werk: |
volume:110 ; year:2021 ; pages:0 |
| Links: |
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| DOI / URN: |
10.1016/j.ast.2021.106489 |
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| 520 | |a Optical devices equipped in supersonic flight vehicles are subjected to distortions of optical paths due to aero-optical effects, potentially resulting in the degradation of sensing and imaging performance. In this study, the aero-optical effects of the supersonic flow over a two-dimensional compression ramp are investigated through experimental and numerical methods. The experiment is conducted by measuring the wavefront of the laser beam propagated through the test section of a supersonic wind tunnel using a two-dimensional Shack-Hartmann sensor. The individual contribution of the shock wave and boundary layer to the wavefront distortion is identified by conducting a ray-tracing computation through the density of the flow field obtained from a two-dimensional numerical simulation that solves the Reynolds-averaged Navier-Stokes equations. The numerically-obtained wavefront is compared with the time-averaged wavefront measured using the Shack-Hartmann sensor. The deflection angle of the ray at the center of the laser beam is analyzed to assess the aero-optical effects caused by the shock wave and boundary layer. The individual contribution of the shock wave and boundary layer to the wavefront distortion was analyzed for various incidence angles of the laser beam. For the present experimental setup, as boundary layers at the top and bottom walls have the opposite direction of the density gradient, the resultant laser beam deflections are mostly governed by the density gradient across the shock wave. | ||
| 520 | |a Optical devices equipped in supersonic flight vehicles are subjected to distortions of optical paths due to aero-optical effects, potentially resulting in the degradation of sensing and imaging performance. In this study, the aero-optical effects of the supersonic flow over a two-dimensional compression ramp are investigated through experimental and numerical methods. The experiment is conducted by measuring the wavefront of the laser beam propagated through the test section of a supersonic wind tunnel using a two-dimensional Shack-Hartmann sensor. The individual contribution of the shock wave and boundary layer to the wavefront distortion is identified by conducting a ray-tracing computation through the density of the flow field obtained from a two-dimensional numerical simulation that solves the Reynolds-averaged Navier-Stokes equations. The numerically-obtained wavefront is compared with the time-averaged wavefront measured using the Shack-Hartmann sensor. The deflection angle of the ray at the center of the laser beam is analyzed to assess the aero-optical effects caused by the shock wave and boundary layer. The individual contribution of the shock wave and boundary layer to the wavefront distortion was analyzed for various incidence angles of the laser beam. For the present experimental setup, as boundary layers at the top and bottom walls have the opposite direction of the density gradient, the resultant laser beam deflections are mostly governed by the density gradient across the shock wave. | ||
| 650 | 7 | |a Supersonic flow |2 Elsevier | |
| 650 | 7 | |a Wavefront measurement |2 Elsevier | |
| 650 | 7 | |a Ray-tracing computation |2 Elsevier | |
| 650 | 7 | |a Aero-optics |2 Elsevier | |
| 650 | 7 | |a Shock wave |2 Elsevier | |
| 700 | 1 | |a Lee, Bok Jik |4 oth | |
| 700 | 1 | |a Jeung, In-Seuck |4 oth | |
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10.1016/j.ast.2021.106489 doi /cbs_pica/cbs_olc/import_discovery/elsevier/einzuspielen/GBV00000000001301.pica (DE-627)ELV053139992 (ELSEVIER)S1270-9638(21)00001-8 DE-627 ger DE-627 rakwb eng 610 VZ 600 670 VZ 51.00 bkl Lee, Sangyoon verfasserin aut Wavefront distortion due to the shock wave and boundary layer in the supersonic flow over a compression ramp 2021transfer abstract nicht spezifiziert zzz rdacontent nicht spezifiziert z rdamedia nicht spezifiziert zu rdacarrier Optical devices equipped in supersonic flight vehicles are subjected to distortions of optical paths due to aero-optical effects, potentially resulting in the degradation of sensing and imaging performance. In this study, the aero-optical effects of the supersonic flow over a two-dimensional compression ramp are investigated through experimental and numerical methods. The experiment is conducted by measuring the wavefront of the laser beam propagated through the test section of a supersonic wind tunnel using a two-dimensional Shack-Hartmann sensor. The individual contribution of the shock wave and boundary layer to the wavefront distortion is identified by conducting a ray-tracing computation through the density of the flow field obtained from a two-dimensional numerical simulation that solves the Reynolds-averaged Navier-Stokes equations. The numerically-obtained wavefront is compared with the time-averaged wavefront measured using the Shack-Hartmann sensor. The deflection angle of the ray at the center of the laser beam is analyzed to assess the aero-optical effects caused by the shock wave and boundary layer. The individual contribution of the shock wave and boundary layer to the wavefront distortion was analyzed for various incidence angles of the laser beam. For the present experimental setup, as boundary layers at the top and bottom walls have the opposite direction of the density gradient, the resultant laser beam deflections are mostly governed by the density gradient across the shock wave. Optical devices equipped in supersonic flight vehicles are subjected to distortions of optical paths due to aero-optical effects, potentially resulting in the degradation of sensing and imaging performance. In this study, the aero-optical effects of the supersonic flow over a two-dimensional compression ramp are investigated through experimental and numerical methods. The experiment is conducted by measuring the wavefront of the laser beam propagated through the test section of a supersonic wind tunnel using a two-dimensional Shack-Hartmann sensor. The individual contribution of the shock wave and boundary layer to the wavefront distortion is identified by conducting a ray-tracing computation through the density of the flow field obtained from a two-dimensional numerical simulation that solves the Reynolds-averaged Navier-Stokes equations. The numerically-obtained wavefront is compared with the time-averaged wavefront measured using the Shack-Hartmann sensor. The deflection angle of the ray at the center of the laser beam is analyzed to assess the aero-optical effects caused by the shock wave and boundary layer. The individual contribution of the shock wave and boundary layer to the wavefront distortion was analyzed for various incidence angles of the laser beam. For the present experimental setup, as boundary layers at the top and bottom walls have the opposite direction of the density gradient, the resultant laser beam deflections are mostly governed by the density gradient across the shock wave. Supersonic flow Elsevier Wavefront measurement Elsevier Ray-tracing computation Elsevier Aero-optics Elsevier Shock wave Elsevier Lee, Bok Jik oth Jeung, In-Seuck oth Enthalten in Elsevier Science Baysal, Birol ELSEVIER Mo1474 The Role of EUS Examination and EUS-Guided Fine Needle Aspiration Biopsy for Evaluation of Gastric Subepithelial Lesions: a Large Single Center Experience 2015 Amsterdam [u.a.] (DE-627)ELV013466232 volume:110 year:2021 pages:0 https://doi.org/10.1016/j.ast.2021.106489 Volltext GBV_USEFLAG_U GBV_ELV SYSFLAG_U GBV_ILN_40 51.00 Werkstoffkunde: Allgemeines VZ AR 110 2021 0 |
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10.1016/j.ast.2021.106489 doi /cbs_pica/cbs_olc/import_discovery/elsevier/einzuspielen/GBV00000000001301.pica (DE-627)ELV053139992 (ELSEVIER)S1270-9638(21)00001-8 DE-627 ger DE-627 rakwb eng 610 VZ 600 670 VZ 51.00 bkl Lee, Sangyoon verfasserin aut Wavefront distortion due to the shock wave and boundary layer in the supersonic flow over a compression ramp 2021transfer abstract nicht spezifiziert zzz rdacontent nicht spezifiziert z rdamedia nicht spezifiziert zu rdacarrier Optical devices equipped in supersonic flight vehicles are subjected to distortions of optical paths due to aero-optical effects, potentially resulting in the degradation of sensing and imaging performance. In this study, the aero-optical effects of the supersonic flow over a two-dimensional compression ramp are investigated through experimental and numerical methods. The experiment is conducted by measuring the wavefront of the laser beam propagated through the test section of a supersonic wind tunnel using a two-dimensional Shack-Hartmann sensor. The individual contribution of the shock wave and boundary layer to the wavefront distortion is identified by conducting a ray-tracing computation through the density of the flow field obtained from a two-dimensional numerical simulation that solves the Reynolds-averaged Navier-Stokes equations. The numerically-obtained wavefront is compared with the time-averaged wavefront measured using the Shack-Hartmann sensor. The deflection angle of the ray at the center of the laser beam is analyzed to assess the aero-optical effects caused by the shock wave and boundary layer. The individual contribution of the shock wave and boundary layer to the wavefront distortion was analyzed for various incidence angles of the laser beam. For the present experimental setup, as boundary layers at the top and bottom walls have the opposite direction of the density gradient, the resultant laser beam deflections are mostly governed by the density gradient across the shock wave. Optical devices equipped in supersonic flight vehicles are subjected to distortions of optical paths due to aero-optical effects, potentially resulting in the degradation of sensing and imaging performance. In this study, the aero-optical effects of the supersonic flow over a two-dimensional compression ramp are investigated through experimental and numerical methods. The experiment is conducted by measuring the wavefront of the laser beam propagated through the test section of a supersonic wind tunnel using a two-dimensional Shack-Hartmann sensor. The individual contribution of the shock wave and boundary layer to the wavefront distortion is identified by conducting a ray-tracing computation through the density of the flow field obtained from a two-dimensional numerical simulation that solves the Reynolds-averaged Navier-Stokes equations. The numerically-obtained wavefront is compared with the time-averaged wavefront measured using the Shack-Hartmann sensor. The deflection angle of the ray at the center of the laser beam is analyzed to assess the aero-optical effects caused by the shock wave and boundary layer. The individual contribution of the shock wave and boundary layer to the wavefront distortion was analyzed for various incidence angles of the laser beam. For the present experimental setup, as boundary layers at the top and bottom walls have the opposite direction of the density gradient, the resultant laser beam deflections are mostly governed by the density gradient across the shock wave. Supersonic flow Elsevier Wavefront measurement Elsevier Ray-tracing computation Elsevier Aero-optics Elsevier Shock wave Elsevier Lee, Bok Jik oth Jeung, In-Seuck oth Enthalten in Elsevier Science Baysal, Birol ELSEVIER Mo1474 The Role of EUS Examination and EUS-Guided Fine Needle Aspiration Biopsy for Evaluation of Gastric Subepithelial Lesions: a Large Single Center Experience 2015 Amsterdam [u.a.] (DE-627)ELV013466232 volume:110 year:2021 pages:0 https://doi.org/10.1016/j.ast.2021.106489 Volltext GBV_USEFLAG_U GBV_ELV SYSFLAG_U GBV_ILN_40 51.00 Werkstoffkunde: Allgemeines VZ AR 110 2021 0 |
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10.1016/j.ast.2021.106489 doi /cbs_pica/cbs_olc/import_discovery/elsevier/einzuspielen/GBV00000000001301.pica (DE-627)ELV053139992 (ELSEVIER)S1270-9638(21)00001-8 DE-627 ger DE-627 rakwb eng 610 VZ 600 670 VZ 51.00 bkl Lee, Sangyoon verfasserin aut Wavefront distortion due to the shock wave and boundary layer in the supersonic flow over a compression ramp 2021transfer abstract nicht spezifiziert zzz rdacontent nicht spezifiziert z rdamedia nicht spezifiziert zu rdacarrier Optical devices equipped in supersonic flight vehicles are subjected to distortions of optical paths due to aero-optical effects, potentially resulting in the degradation of sensing and imaging performance. In this study, the aero-optical effects of the supersonic flow over a two-dimensional compression ramp are investigated through experimental and numerical methods. The experiment is conducted by measuring the wavefront of the laser beam propagated through the test section of a supersonic wind tunnel using a two-dimensional Shack-Hartmann sensor. The individual contribution of the shock wave and boundary layer to the wavefront distortion is identified by conducting a ray-tracing computation through the density of the flow field obtained from a two-dimensional numerical simulation that solves the Reynolds-averaged Navier-Stokes equations. The numerically-obtained wavefront is compared with the time-averaged wavefront measured using the Shack-Hartmann sensor. The deflection angle of the ray at the center of the laser beam is analyzed to assess the aero-optical effects caused by the shock wave and boundary layer. The individual contribution of the shock wave and boundary layer to the wavefront distortion was analyzed for various incidence angles of the laser beam. For the present experimental setup, as boundary layers at the top and bottom walls have the opposite direction of the density gradient, the resultant laser beam deflections are mostly governed by the density gradient across the shock wave. Optical devices equipped in supersonic flight vehicles are subjected to distortions of optical paths due to aero-optical effects, potentially resulting in the degradation of sensing and imaging performance. In this study, the aero-optical effects of the supersonic flow over a two-dimensional compression ramp are investigated through experimental and numerical methods. The experiment is conducted by measuring the wavefront of the laser beam propagated through the test section of a supersonic wind tunnel using a two-dimensional Shack-Hartmann sensor. The individual contribution of the shock wave and boundary layer to the wavefront distortion is identified by conducting a ray-tracing computation through the density of the flow field obtained from a two-dimensional numerical simulation that solves the Reynolds-averaged Navier-Stokes equations. The numerically-obtained wavefront is compared with the time-averaged wavefront measured using the Shack-Hartmann sensor. The deflection angle of the ray at the center of the laser beam is analyzed to assess the aero-optical effects caused by the shock wave and boundary layer. The individual contribution of the shock wave and boundary layer to the wavefront distortion was analyzed for various incidence angles of the laser beam. For the present experimental setup, as boundary layers at the top and bottom walls have the opposite direction of the density gradient, the resultant laser beam deflections are mostly governed by the density gradient across the shock wave. Supersonic flow Elsevier Wavefront measurement Elsevier Ray-tracing computation Elsevier Aero-optics Elsevier Shock wave Elsevier Lee, Bok Jik oth Jeung, In-Seuck oth Enthalten in Elsevier Science Baysal, Birol ELSEVIER Mo1474 The Role of EUS Examination and EUS-Guided Fine Needle Aspiration Biopsy for Evaluation of Gastric Subepithelial Lesions: a Large Single Center Experience 2015 Amsterdam [u.a.] (DE-627)ELV013466232 volume:110 year:2021 pages:0 https://doi.org/10.1016/j.ast.2021.106489 Volltext GBV_USEFLAG_U GBV_ELV SYSFLAG_U GBV_ILN_40 51.00 Werkstoffkunde: Allgemeines VZ AR 110 2021 0 |
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10.1016/j.ast.2021.106489 doi /cbs_pica/cbs_olc/import_discovery/elsevier/einzuspielen/GBV00000000001301.pica (DE-627)ELV053139992 (ELSEVIER)S1270-9638(21)00001-8 DE-627 ger DE-627 rakwb eng 610 VZ 600 670 VZ 51.00 bkl Lee, Sangyoon verfasserin aut Wavefront distortion due to the shock wave and boundary layer in the supersonic flow over a compression ramp 2021transfer abstract nicht spezifiziert zzz rdacontent nicht spezifiziert z rdamedia nicht spezifiziert zu rdacarrier Optical devices equipped in supersonic flight vehicles are subjected to distortions of optical paths due to aero-optical effects, potentially resulting in the degradation of sensing and imaging performance. In this study, the aero-optical effects of the supersonic flow over a two-dimensional compression ramp are investigated through experimental and numerical methods. The experiment is conducted by measuring the wavefront of the laser beam propagated through the test section of a supersonic wind tunnel using a two-dimensional Shack-Hartmann sensor. The individual contribution of the shock wave and boundary layer to the wavefront distortion is identified by conducting a ray-tracing computation through the density of the flow field obtained from a two-dimensional numerical simulation that solves the Reynolds-averaged Navier-Stokes equations. The numerically-obtained wavefront is compared with the time-averaged wavefront measured using the Shack-Hartmann sensor. The deflection angle of the ray at the center of the laser beam is analyzed to assess the aero-optical effects caused by the shock wave and boundary layer. The individual contribution of the shock wave and boundary layer to the wavefront distortion was analyzed for various incidence angles of the laser beam. For the present experimental setup, as boundary layers at the top and bottom walls have the opposite direction of the density gradient, the resultant laser beam deflections are mostly governed by the density gradient across the shock wave. Optical devices equipped in supersonic flight vehicles are subjected to distortions of optical paths due to aero-optical effects, potentially resulting in the degradation of sensing and imaging performance. In this study, the aero-optical effects of the supersonic flow over a two-dimensional compression ramp are investigated through experimental and numerical methods. The experiment is conducted by measuring the wavefront of the laser beam propagated through the test section of a supersonic wind tunnel using a two-dimensional Shack-Hartmann sensor. The individual contribution of the shock wave and boundary layer to the wavefront distortion is identified by conducting a ray-tracing computation through the density of the flow field obtained from a two-dimensional numerical simulation that solves the Reynolds-averaged Navier-Stokes equations. The numerically-obtained wavefront is compared with the time-averaged wavefront measured using the Shack-Hartmann sensor. The deflection angle of the ray at the center of the laser beam is analyzed to assess the aero-optical effects caused by the shock wave and boundary layer. The individual contribution of the shock wave and boundary layer to the wavefront distortion was analyzed for various incidence angles of the laser beam. For the present experimental setup, as boundary layers at the top and bottom walls have the opposite direction of the density gradient, the resultant laser beam deflections are mostly governed by the density gradient across the shock wave. Supersonic flow Elsevier Wavefront measurement Elsevier Ray-tracing computation Elsevier Aero-optics Elsevier Shock wave Elsevier Lee, Bok Jik oth Jeung, In-Seuck oth Enthalten in Elsevier Science Baysal, Birol ELSEVIER Mo1474 The Role of EUS Examination and EUS-Guided Fine Needle Aspiration Biopsy for Evaluation of Gastric Subepithelial Lesions: a Large Single Center Experience 2015 Amsterdam [u.a.] (DE-627)ELV013466232 volume:110 year:2021 pages:0 https://doi.org/10.1016/j.ast.2021.106489 Volltext GBV_USEFLAG_U GBV_ELV SYSFLAG_U GBV_ILN_40 51.00 Werkstoffkunde: Allgemeines VZ AR 110 2021 0 |
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10.1016/j.ast.2021.106489 doi /cbs_pica/cbs_olc/import_discovery/elsevier/einzuspielen/GBV00000000001301.pica (DE-627)ELV053139992 (ELSEVIER)S1270-9638(21)00001-8 DE-627 ger DE-627 rakwb eng 610 VZ 600 670 VZ 51.00 bkl Lee, Sangyoon verfasserin aut Wavefront distortion due to the shock wave and boundary layer in the supersonic flow over a compression ramp 2021transfer abstract nicht spezifiziert zzz rdacontent nicht spezifiziert z rdamedia nicht spezifiziert zu rdacarrier Optical devices equipped in supersonic flight vehicles are subjected to distortions of optical paths due to aero-optical effects, potentially resulting in the degradation of sensing and imaging performance. In this study, the aero-optical effects of the supersonic flow over a two-dimensional compression ramp are investigated through experimental and numerical methods. The experiment is conducted by measuring the wavefront of the laser beam propagated through the test section of a supersonic wind tunnel using a two-dimensional Shack-Hartmann sensor. The individual contribution of the shock wave and boundary layer to the wavefront distortion is identified by conducting a ray-tracing computation through the density of the flow field obtained from a two-dimensional numerical simulation that solves the Reynolds-averaged Navier-Stokes equations. The numerically-obtained wavefront is compared with the time-averaged wavefront measured using the Shack-Hartmann sensor. The deflection angle of the ray at the center of the laser beam is analyzed to assess the aero-optical effects caused by the shock wave and boundary layer. The individual contribution of the shock wave and boundary layer to the wavefront distortion was analyzed for various incidence angles of the laser beam. For the present experimental setup, as boundary layers at the top and bottom walls have the opposite direction of the density gradient, the resultant laser beam deflections are mostly governed by the density gradient across the shock wave. Optical devices equipped in supersonic flight vehicles are subjected to distortions of optical paths due to aero-optical effects, potentially resulting in the degradation of sensing and imaging performance. In this study, the aero-optical effects of the supersonic flow over a two-dimensional compression ramp are investigated through experimental and numerical methods. The experiment is conducted by measuring the wavefront of the laser beam propagated through the test section of a supersonic wind tunnel using a two-dimensional Shack-Hartmann sensor. The individual contribution of the shock wave and boundary layer to the wavefront distortion is identified by conducting a ray-tracing computation through the density of the flow field obtained from a two-dimensional numerical simulation that solves the Reynolds-averaged Navier-Stokes equations. The numerically-obtained wavefront is compared with the time-averaged wavefront measured using the Shack-Hartmann sensor. The deflection angle of the ray at the center of the laser beam is analyzed to assess the aero-optical effects caused by the shock wave and boundary layer. The individual contribution of the shock wave and boundary layer to the wavefront distortion was analyzed for various incidence angles of the laser beam. For the present experimental setup, as boundary layers at the top and bottom walls have the opposite direction of the density gradient, the resultant laser beam deflections are mostly governed by the density gradient across the shock wave. Supersonic flow Elsevier Wavefront measurement Elsevier Ray-tracing computation Elsevier Aero-optics Elsevier Shock wave Elsevier Lee, Bok Jik oth Jeung, In-Seuck oth Enthalten in Elsevier Science Baysal, Birol ELSEVIER Mo1474 The Role of EUS Examination and EUS-Guided Fine Needle Aspiration Biopsy for Evaluation of Gastric Subepithelial Lesions: a Large Single Center Experience 2015 Amsterdam [u.a.] (DE-627)ELV013466232 volume:110 year:2021 pages:0 https://doi.org/10.1016/j.ast.2021.106489 Volltext GBV_USEFLAG_U GBV_ELV SYSFLAG_U GBV_ILN_40 51.00 Werkstoffkunde: Allgemeines VZ AR 110 2021 0 |
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wavefront distortion due to the shock wave and boundary layer in the supersonic flow over a compression ramp |
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Wavefront distortion due to the shock wave and boundary layer in the supersonic flow over a compression ramp |
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Optical devices equipped in supersonic flight vehicles are subjected to distortions of optical paths due to aero-optical effects, potentially resulting in the degradation of sensing and imaging performance. In this study, the aero-optical effects of the supersonic flow over a two-dimensional compression ramp are investigated through experimental and numerical methods. The experiment is conducted by measuring the wavefront of the laser beam propagated through the test section of a supersonic wind tunnel using a two-dimensional Shack-Hartmann sensor. The individual contribution of the shock wave and boundary layer to the wavefront distortion is identified by conducting a ray-tracing computation through the density of the flow field obtained from a two-dimensional numerical simulation that solves the Reynolds-averaged Navier-Stokes equations. The numerically-obtained wavefront is compared with the time-averaged wavefront measured using the Shack-Hartmann sensor. The deflection angle of the ray at the center of the laser beam is analyzed to assess the aero-optical effects caused by the shock wave and boundary layer. The individual contribution of the shock wave and boundary layer to the wavefront distortion was analyzed for various incidence angles of the laser beam. For the present experimental setup, as boundary layers at the top and bottom walls have the opposite direction of the density gradient, the resultant laser beam deflections are mostly governed by the density gradient across the shock wave. |
| abstractGer |
Optical devices equipped in supersonic flight vehicles are subjected to distortions of optical paths due to aero-optical effects, potentially resulting in the degradation of sensing and imaging performance. In this study, the aero-optical effects of the supersonic flow over a two-dimensional compression ramp are investigated through experimental and numerical methods. The experiment is conducted by measuring the wavefront of the laser beam propagated through the test section of a supersonic wind tunnel using a two-dimensional Shack-Hartmann sensor. The individual contribution of the shock wave and boundary layer to the wavefront distortion is identified by conducting a ray-tracing computation through the density of the flow field obtained from a two-dimensional numerical simulation that solves the Reynolds-averaged Navier-Stokes equations. The numerically-obtained wavefront is compared with the time-averaged wavefront measured using the Shack-Hartmann sensor. The deflection angle of the ray at the center of the laser beam is analyzed to assess the aero-optical effects caused by the shock wave and boundary layer. The individual contribution of the shock wave and boundary layer to the wavefront distortion was analyzed for various incidence angles of the laser beam. For the present experimental setup, as boundary layers at the top and bottom walls have the opposite direction of the density gradient, the resultant laser beam deflections are mostly governed by the density gradient across the shock wave. |
| abstract_unstemmed |
Optical devices equipped in supersonic flight vehicles are subjected to distortions of optical paths due to aero-optical effects, potentially resulting in the degradation of sensing and imaging performance. In this study, the aero-optical effects of the supersonic flow over a two-dimensional compression ramp are investigated through experimental and numerical methods. The experiment is conducted by measuring the wavefront of the laser beam propagated through the test section of a supersonic wind tunnel using a two-dimensional Shack-Hartmann sensor. The individual contribution of the shock wave and boundary layer to the wavefront distortion is identified by conducting a ray-tracing computation through the density of the flow field obtained from a two-dimensional numerical simulation that solves the Reynolds-averaged Navier-Stokes equations. The numerically-obtained wavefront is compared with the time-averaged wavefront measured using the Shack-Hartmann sensor. The deflection angle of the ray at the center of the laser beam is analyzed to assess the aero-optical effects caused by the shock wave and boundary layer. The individual contribution of the shock wave and boundary layer to the wavefront distortion was analyzed for various incidence angles of the laser beam. For the present experimental setup, as boundary layers at the top and bottom walls have the opposite direction of the density gradient, the resultant laser beam deflections are mostly governed by the density gradient across the shock wave. |
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