CALCULATION OF ROCKET NOSE FAIRING SHELLS AERODYNAMIC CHARACTERISTICS
The aerodynamic characteristics of the detachable elements of transport systems are introduced, they allow to calculate the trajectories of these elements after their separation and determine the size of elements impact areas. Special consideration is given to head fairing shells, containing cylindr...
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| Format: | Article |
| Language: | Russian |
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Moscow State Technical University of Civil Aviation
2018-03-01
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| Series: | Научный вестник МГТУ ГА |
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| Online Access: | https://avia.mstuca.ru/jour/article/view/1180 |
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| _version_ | 1849252714638213120 |
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| author | V. T. Kalugin A. Y. Lutsenko D. K. Nazarova |
| author_facet | V. T. Kalugin A. Y. Lutsenko D. K. Nazarova |
| author_sort | V. T. Kalugin |
| collection | DOAJ |
| description | The aerodynamic characteristics of the detachable elements of transport systems are introduced, they allow to calculate the trajectories of these elements after their separation and determine the size of elements impact areas. Special consideration is given to head fairing shells, containing cylindrical, conical and spherical sections. Head fairing shells have high lift-to-drag ratio and the widest impact areas. Aerodynamics of bodies of such configurations has been insufficiently studied. The paper presents the numerical results of modeling the flow around a typical head fairing shell in free flight. Open source OpenFOAM package is used for numerical simulation. The aerodynamic characteristics at trans- and supersonic velocities are obtained, flow pattern transformation with the change of the angle of attack and Mach number is analyzed. The possibility of OpenFOAM package for aerodynamic calculations of thin shells is shown. The analysis of the obtained results demonstrate that there are many complex shock waves interacting with each other at flow supersonic speeds, at subsonic speeds vast regions of flow separations are observed. The authors identify intervals of angles of attack, where different types of flow structures are realized, both for trans- and supersonic flow speeds. The flow pattern change affects the aerodynamic characteristics, the aerodynamic coefficients significantly change with increase of the angle of attack. There are two trim angles of attack at all examined flow velocities. The results obtained can be used to develop a passive stabilization system for fairing shell that will balance the body at the angle of attack with minimum lift-to-drag ratio and will reduce random deviations. |
| format | Article |
| id | doaj-art-bbf56485f3854db692810670e4c19058 |
| institution | Kabale University |
| issn | 2079-0619 2542-0119 |
| language | Russian |
| publishDate | 2018-03-01 |
| publisher | Moscow State Technical University of Civil Aviation |
| record_format | Article |
| series | Научный вестник МГТУ ГА |
| spelling | doaj-art-bbf56485f3854db692810670e4c190582025-08-20T03:56:33ZrusMoscow State Technical University of Civil AviationНаучный вестник МГТУ ГА2079-06192542-01192018-03-01211222910.26467/2079-0619-2018-21-1-22-291161CALCULATION OF ROCKET NOSE FAIRING SHELLS AERODYNAMIC CHARACTERISTICSV. T. Kalugin0A. Y. Lutsenko1D. K. Nazarova2Bauman Moscow State Technical UniversityBauman Moscow State Technical UniversityBauman Moscow State Technical UniversityThe aerodynamic characteristics of the detachable elements of transport systems are introduced, they allow to calculate the trajectories of these elements after their separation and determine the size of elements impact areas. Special consideration is given to head fairing shells, containing cylindrical, conical and spherical sections. Head fairing shells have high lift-to-drag ratio and the widest impact areas. Aerodynamics of bodies of such configurations has been insufficiently studied. The paper presents the numerical results of modeling the flow around a typical head fairing shell in free flight. Open source OpenFOAM package is used for numerical simulation. The aerodynamic characteristics at trans- and supersonic velocities are obtained, flow pattern transformation with the change of the angle of attack and Mach number is analyzed. The possibility of OpenFOAM package for aerodynamic calculations of thin shells is shown. The analysis of the obtained results demonstrate that there are many complex shock waves interacting with each other at flow supersonic speeds, at subsonic speeds vast regions of flow separations are observed. The authors identify intervals of angles of attack, where different types of flow structures are realized, both for trans- and supersonic flow speeds. The flow pattern change affects the aerodynamic characteristics, the aerodynamic coefficients significantly change with increase of the angle of attack. There are two trim angles of attack at all examined flow velocities. The results obtained can be used to develop a passive stabilization system for fairing shell that will balance the body at the angle of attack with minimum lift-to-drag ratio and will reduce random deviations.https://avia.mstuca.ru/jour/article/view/1180openfoam |
| spellingShingle | V. T. Kalugin A. Y. Lutsenko D. K. Nazarova CALCULATION OF ROCKET NOSE FAIRING SHELLS AERODYNAMIC CHARACTERISTICS Научный вестник МГТУ ГА openfoam |
| title | CALCULATION OF ROCKET NOSE FAIRING SHELLS AERODYNAMIC CHARACTERISTICS |
| title_full | CALCULATION OF ROCKET NOSE FAIRING SHELLS AERODYNAMIC CHARACTERISTICS |
| title_fullStr | CALCULATION OF ROCKET NOSE FAIRING SHELLS AERODYNAMIC CHARACTERISTICS |
| title_full_unstemmed | CALCULATION OF ROCKET NOSE FAIRING SHELLS AERODYNAMIC CHARACTERISTICS |
| title_short | CALCULATION OF ROCKET NOSE FAIRING SHELLS AERODYNAMIC CHARACTERISTICS |
| title_sort | calculation of rocket nose fairing shells aerodynamic characteristics |
| topic | openfoam |
| url | https://avia.mstuca.ru/jour/article/view/1180 |
| work_keys_str_mv | AT vtkalugin calculationofrocketnosefairingshellsaerodynamiccharacteristics AT aylutsenko calculationofrocketnosefairingshellsaerodynamiccharacteristics AT dknazarova calculationofrocketnosefairingshellsaerodynamiccharacteristics |