A study of high lift aerodynamic devices on commercial aircrafts
Aerodynamic performance of aircraft wings vary with flight path conditions and depend on efficiency of high lift systems. In this work, a study on high lift devices and mechanisms that aim to increase maximum lift coefficient and reduce drag on commercial aircraft wings is discussed. Typically, such...
| Main Authors: | , , |
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| Format: | Article |
| Language: | English |
| Published: |
Vilnius Gediminas Technical University
2020-09-01
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| Series: | Aviation |
| Subjects: | |
| Online Access: | https://journals.vgtu.lt/index.php/Aviation/article/view/12815 |
| _version_ | 1818890935379951616 |
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| author | Swamy Naidu Venkata Neigapula Satya Prasad Maddula Vasishta Bhargava Nukala |
| author_facet | Swamy Naidu Venkata Neigapula Satya Prasad Maddula Vasishta Bhargava Nukala |
| author_sort | Swamy Naidu Venkata Neigapula |
| collection | DOAJ |
| description | Aerodynamic performance of aircraft wings vary with flight path conditions and depend on efficiency of high lift systems. In this work, a study on high lift devices and mechanisms that aim to increase maximum lift coefficient and reduce drag on commercial aircraft wings is discussed. Typically, such extensions are provided to main airfoil along span wise direction of wing and can increase lift coefficient by more than 100% during operation. Increasing the no of trailing edge flaps in chord wise direction could result in 100% increment in lift coefficient at a given angle of attack but leading edge slats improve lift by delaying the flow separation near stall angle of attack. Different combinations of trailing edge flaps used by Airbus, Boeing and McDonnel Douglas manufacturers are explained along with kinematic mechanisms to deploy them. The surface pressure distribution for 30P30N airfoil is evaluated using 2D vortex panel method and effects of chord wise boundary layer flow transitions on aerodynamic lift generation is discussed. The results showed better agreements with experiment data for high Reynolds number (9 million) flow conditions near stall angle of attack. |
| first_indexed | 2024-12-19T17:32:49Z |
| format | Article |
| id | doaj.art-cfd4185cf6a04bea8799ad3e98f6274e |
| institution | Directory Open Access Journal |
| issn | 1648-7788 1822-4180 |
| language | English |
| last_indexed | 2024-12-19T17:32:49Z |
| publishDate | 2020-09-01 |
| publisher | Vilnius Gediminas Technical University |
| record_format | Article |
| series | Aviation |
| spelling | doaj.art-cfd4185cf6a04bea8799ad3e98f6274e2022-12-21T20:12:24ZengVilnius Gediminas Technical UniversityAviation1648-77881822-41802020-09-0124310.3846/aviation.2020.12815A study of high lift aerodynamic devices on commercial aircraftsSwamy Naidu Venkata Neigapula0Satya Prasad Maddula1Vasishta Bhargava Nukala 2Department of Mechanical Engineering, National Institute of Technology, Raipur, IndiaDepartment of Aerospace Engineering, GITAM University, Hyderabad, IndiaDepartment of Mechanical Engineering, Sreyas Institute of Engineering and Technology, Nagole, Hyderabad, IndiaAerodynamic performance of aircraft wings vary with flight path conditions and depend on efficiency of high lift systems. In this work, a study on high lift devices and mechanisms that aim to increase maximum lift coefficient and reduce drag on commercial aircraft wings is discussed. Typically, such extensions are provided to main airfoil along span wise direction of wing and can increase lift coefficient by more than 100% during operation. Increasing the no of trailing edge flaps in chord wise direction could result in 100% increment in lift coefficient at a given angle of attack but leading edge slats improve lift by delaying the flow separation near stall angle of attack. Different combinations of trailing edge flaps used by Airbus, Boeing and McDonnel Douglas manufacturers are explained along with kinematic mechanisms to deploy them. The surface pressure distribution for 30P30N airfoil is evaluated using 2D vortex panel method and effects of chord wise boundary layer flow transitions on aerodynamic lift generation is discussed. The results showed better agreements with experiment data for high Reynolds number (9 million) flow conditions near stall angle of attack.https://journals.vgtu.lt/index.php/Aviation/article/view/12815flapslataircraft winghigh liftaerofoildrag |
| spellingShingle | Swamy Naidu Venkata Neigapula Satya Prasad Maddula Vasishta Bhargava Nukala A study of high lift aerodynamic devices on commercial aircrafts Aviation flap slat aircraft wing high lift aerofoil drag |
| title | A study of high lift aerodynamic devices on commercial aircrafts |
| title_full | A study of high lift aerodynamic devices on commercial aircrafts |
| title_fullStr | A study of high lift aerodynamic devices on commercial aircrafts |
| title_full_unstemmed | A study of high lift aerodynamic devices on commercial aircrafts |
| title_short | A study of high lift aerodynamic devices on commercial aircrafts |
| title_sort | study of high lift aerodynamic devices on commercial aircrafts |
| topic | flap slat aircraft wing high lift aerofoil drag |
| url | https://journals.vgtu.lt/index.php/Aviation/article/view/12815 |
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