Simulation of the Effect of the Main Wing on the Tail Differential Pressure Force of an Aircraft Based on the Spalart-Allmaras Model

DOI

10.2991/978-94-6463-518-8_3How to use a DOI?

Keywords

Ansys Fluent; main wing; tail; Spalart-Allmaras; vortex shedding

Abstract

To investigate the characteristics of the differential pressure force on the tailplane which is in the trailing edge of the main wing. In this paper, Ansys Fluent software is used to simulate the characteristics of the differential pressure force on the tailplane when aircraft with different tail heights are performing 15° elevation manoeuvres. In this paper, the main wing of the aircraft adopts the NACA2412 airfoil and is simulated using the Spalart-Allmaras model. The results show that the obstruction effect of the main wing on the airflow, as well as the vortex at the rear end of the main wing can greatly affect the pressure distribution on the tail surface. In particular, the flow field near the wake cannot reach a steady state but fluctuates within a certain range, and the position of the wake has a strong relationship with the mean value of the fluctuation and the intensity of the fluctuation. In addition, the lift applied to the tail in the wake varies significantly, and the lift applied to the tail is larger when it is at the lower boundary of the main wing wake and in the middle of the wake. This study fills the gap of research in the related field and provides help for the aerodynamic shape design of small aircraft.

Copyright

© 2024 The Author(s)

Open Access

Open Access This chapter is licensed under the terms of the Creative Commons Attribution-NonCommercial 4.0 International License (http://creativecommons.org/licenses/by-nc/4.0/), which permits any noncommercial use, sharing, adaptation, distribution and reproduction in any medium or format, as long as you give appropriate credit to the original author(s) and the source, provide a link to the Creative Commons license and indicate if changes were made.

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TY  - CONF
AU  - Jialuo Hong
PY  - 2024
DA  - 2024/09/28
TI  - Simulation of the Effect of the Main Wing on the Tail Differential Pressure Force of an Aircraft Based on the Spalart-Allmaras Model
BT  - Proceedings of the 2024 International Conference on Mechanics, Electronics Engineering and Automation (ICMEEA 2024)
PB  - Atlantis Press
SP  - 13
EP  - 26
SN  - 2352-5401
UR  - https://doi.org/10.2991/978-94-6463-518-8_3
DO  - 10.2991/978-94-6463-518-8_3
ID  - Hong2024
ER  -