Numerical simulation of the unsteady aerodynamic loads on the tail fin in the vortex breakdown flow
by Andrey Epikhin
Progress in Computational Fluid Dynamics, An International Journal (PCFD), Vol. 21, No. 5, 2021

Abstract: This work presents numerical simulation results of the flow around an airbrake-tail fin system of an aircraft. In this research, airbrake location and deflection angles effects on the unsteady aerodynamic loads acting on the tail fin that leads to the buffeting have been studied. The main flow field structures and their transformation features are investigated. The area of the maximal pressure applied to the tail fin has been determined. Analysing the obtained data during a series of numerical simulations allows to conclude that aerodynamic loads on the tail fin increase by five times. This conclusion has been made for the considered configuration of the airbrake-tail fin system when the airbrake deflection angle grows bigger. Change in the distance between the airbrake and the tail fin does not significantly affect the force loads. The efficiency of using the airbrake under different operating conditions has been estimated.

Online publication date: Tue, 07-Sep-2021

The full text of this article is only available to individual subscribers or to users at subscribing institutions.

Existing subscribers:
Go to Inderscience Online Journals to access the Full Text of this article.

Pay per view:
If you are not a subscriber and you just want to read the full contents of this article, buy online access here.

Complimentary Subscribers, Editors or Members of the Editorial Board of the Progress in Computational Fluid Dynamics, An International Journal (PCFD):
Login with your Inderscience username and password:

    Username:        Password:         

Forgotten your password?

Want to subscribe?
A subscription gives you complete access to all articles in the current issue, as well as to all articles in the previous three years (where applicable). See our Orders page to subscribe.

If you still need assistance, please email