An Aerodynamic Design Method to Improve the High-Speed Performance of a Low-Aspect-Ratio Tailless Aircraft
This paper puts forward an aerodynamic design method to improve the high-speed aerodynamic performance of an aircraft with low-aspect-ratio tailless configuration. The method can ameliorate the longitudinal moment characteristics of the configuration by designing and collocating the key section airf...
| Main Authors: | , , |
|---|---|
| Format: | Article |
| Language: | English |
| Published: |
MDPI AG
2021-02-01
|
| Series: | Applied Sciences |
| Subjects: | |
| Online Access: | https://www.mdpi.com/2076-3417/11/4/1555 |
| _version_ | 1797412452722278400 |
|---|---|
| author | Zhongyuan Liu Lie Luo Binqian Zhang |
| author_facet | Zhongyuan Liu Lie Luo Binqian Zhang |
| author_sort | Zhongyuan Liu |
| collection | DOAJ |
| description | This paper puts forward an aerodynamic design method to improve the high-speed aerodynamic performance of an aircraft with low-aspect-ratio tailless configuration. The method can ameliorate the longitudinal moment characteristics of the configuration by designing and collocating the key section airfoils with the constrains of fixed parameters of planform shape and capacity. Firstly, the effect of twisting the wing, fore-loading and aft-reflexing key section airfoils on the high-speed aerodynamic performance of the configuration is evaluated by high-fidelity numerical methods, and quantified by defining trimming efficiency factors. Then, a linear superposition formula is obtained by analyzing the effect rule of trimming efficiency factor, and based on the formula the design and collocation methods of key section airfoils are achieved. According to the methods, a trimmed configuration is obtained. The results of computational fluid dynamics (CFD) and wind tunnel tests show that the trimmed configuration has smaller zero-lift pitching moment and higher available lift-to-drag ratio than the initial configuration at cruise, besides the trimmed configuration achieves the design principle raised for tailless configuration, which can be described as the zero-pitching moment, cruising design lift coefficient, and maximum lift-to-drag ratio are coincident. In addition, at off-design conditions, the trimmed configuration shows favorable drag divergence characteristics, satisfactory aerodynamic characteristics at medium-altitude maneuvering condition, and good stall and pitching-moment performance at low speed state. |
| first_indexed | 2024-03-09T05:03:01Z |
| format | Article |
| id | doaj.art-a21857ab45374f6eb808b9704148cb61 |
| institution | Directory Open Access Journal |
| issn | 2076-3417 |
| language | English |
| last_indexed | 2024-03-09T05:03:01Z |
| publishDate | 2021-02-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Applied Sciences |
| spelling | doaj.art-a21857ab45374f6eb808b9704148cb612023-12-03T12:58:07ZengMDPI AGApplied Sciences2076-34172021-02-01114155510.3390/app11041555An Aerodynamic Design Method to Improve the High-Speed Performance of a Low-Aspect-Ratio Tailless AircraftZhongyuan Liu0Lie Luo1Binqian Zhang2School of Aeronautics, Northwestern Polytechnical University, Xi’an 710072, ChinaThe First Aircraft Institute of AVIC, Xi’an 710089, ChinaSchool of Aeronautics, Northwestern Polytechnical University, Xi’an 710072, ChinaThis paper puts forward an aerodynamic design method to improve the high-speed aerodynamic performance of an aircraft with low-aspect-ratio tailless configuration. The method can ameliorate the longitudinal moment characteristics of the configuration by designing and collocating the key section airfoils with the constrains of fixed parameters of planform shape and capacity. Firstly, the effect of twisting the wing, fore-loading and aft-reflexing key section airfoils on the high-speed aerodynamic performance of the configuration is evaluated by high-fidelity numerical methods, and quantified by defining trimming efficiency factors. Then, a linear superposition formula is obtained by analyzing the effect rule of trimming efficiency factor, and based on the formula the design and collocation methods of key section airfoils are achieved. According to the methods, a trimmed configuration is obtained. The results of computational fluid dynamics (CFD) and wind tunnel tests show that the trimmed configuration has smaller zero-lift pitching moment and higher available lift-to-drag ratio than the initial configuration at cruise, besides the trimmed configuration achieves the design principle raised for tailless configuration, which can be described as the zero-pitching moment, cruising design lift coefficient, and maximum lift-to-drag ratio are coincident. In addition, at off-design conditions, the trimmed configuration shows favorable drag divergence characteristics, satisfactory aerodynamic characteristics at medium-altitude maneuvering condition, and good stall and pitching-moment performance at low speed state.https://www.mdpi.com/2076-3417/11/4/1555aerodynamic designlow-aspect-ratio tailless configurationpitching moment |
| spellingShingle | Zhongyuan Liu Lie Luo Binqian Zhang An Aerodynamic Design Method to Improve the High-Speed Performance of a Low-Aspect-Ratio Tailless Aircraft Applied Sciences aerodynamic design low-aspect-ratio tailless configuration pitching moment |
| title | An Aerodynamic Design Method to Improve the High-Speed Performance of a Low-Aspect-Ratio Tailless Aircraft |
| title_full | An Aerodynamic Design Method to Improve the High-Speed Performance of a Low-Aspect-Ratio Tailless Aircraft |
| title_fullStr | An Aerodynamic Design Method to Improve the High-Speed Performance of a Low-Aspect-Ratio Tailless Aircraft |
| title_full_unstemmed | An Aerodynamic Design Method to Improve the High-Speed Performance of a Low-Aspect-Ratio Tailless Aircraft |
| title_short | An Aerodynamic Design Method to Improve the High-Speed Performance of a Low-Aspect-Ratio Tailless Aircraft |
| title_sort | aerodynamic design method to improve the high speed performance of a low aspect ratio tailless aircraft |
| topic | aerodynamic design low-aspect-ratio tailless configuration pitching moment |
| url | https://www.mdpi.com/2076-3417/11/4/1555 |
| work_keys_str_mv | AT zhongyuanliu anaerodynamicdesignmethodtoimprovethehighspeedperformanceofalowaspectratiotaillessaircraft AT lieluo anaerodynamicdesignmethodtoimprovethehighspeedperformanceofalowaspectratiotaillessaircraft AT binqianzhang anaerodynamicdesignmethodtoimprovethehighspeedperformanceofalowaspectratiotaillessaircraft AT zhongyuanliu aerodynamicdesignmethodtoimprovethehighspeedperformanceofalowaspectratiotaillessaircraft AT lieluo aerodynamicdesignmethodtoimprovethehighspeedperformanceofalowaspectratiotaillessaircraft AT binqianzhang aerodynamicdesignmethodtoimprovethehighspeedperformanceofalowaspectratiotaillessaircraft |