- Tytuł:
- Numerical analysis and optimization of a winglet sweep angle and winglet tip chord for improvement of aircraft flight performance
- Autorzy:
-
Al-Khafaji, Ali J. Dawood
Panatov, Gennady S.
Boldyrev, Anton S. - Powiązania:
- https://bibliotekanauki.pl/articles/2096195.pdf
- Data publikacji:
- 2022
- Wydawca:
- Polska Akademia Nauk. Polskie Towarzystwo Diagnostyki Technicznej PAN
- Tematy:
-
lift
drag
lift coefficient
drag coefficient
aircraft wing
winglet
angle of attack
sweep angle
SOLIDWORKS
CFD
ANSYS FLUENT
współczynnik siły nośnej
współczynnik oporu
skrzydło samolotu
skrzydełko aerodynamiczne
kąt natarcia
SolidWorks
ANSYS Fluent - Opis:
- In this paper, a study of the effect of winglet sweep angle and winglet tip chord of the aircraft wing on the aerodynamics performances and how to improve it are carried out, assuming Cant angle 60°, winglet height = 3.5 m, Toe angle = -5°, and Twist angle = +5°. Different sweep angles tested (-25°, -15°, 0°, +15°, +25°, +35°, and +45°) and winglet tip chord (0.25, 0.375, and 0.5 m). Four Angle of attack is presented (0°, 3°, 6°, and 9°). The aerodynamics properties of the wing were measured in terms of calculated lift to drag ratio to decide which wing has a high value of lift and lower drag. All models of a wing (eighty-four models) are drawn for 3D using the SOLIDWORKS program. Boeing 737-800 wing dimensions were used. All models of a wing were analyzed using ANSYS FLUENT. The results showed that sweep angle and winglet tip chord of the winglet by changing their configuration can improve aerodynamic performance for various attack angles. The maximum value of the lift to drag ratio was obtained with a sweep angle -15°, winglet tip chord 0.375m, and angle of attack 3°.
- Źródło:
-
Diagnostyka; 2022, 23, 2; art. no. 2022210
1641-6414
2449-5220 - Pojawia się w:
- Diagnostyka
- Dostawca treści:
- Biblioteka Nauki
Artykuł