Transonic flow around the airfoil with aileron at a positive attack angle

Authors

  • Konstantin V. Babarykin St. Petersburg State University, Universitetskaya nab., 7-9, St. Petersburg, 199034, Russian Federation;

Abstract

A numerical investigation of transonic flow around airfoil Whitcomb by well-known CFD program Fluent is carried out. The behavior of lift coefficient in the range of freestream Mach number from 0,81 to 0,86 with aileron deflection is considered. The influence of the aileron deflection degree on the character of supersonic regions forming near airfoil is examined. Evolution of flow structure under a freestream parameters and airfoil form variations, and also the related to it lift coefficient changing are analyzed. Refs 5. Figs 7.

Keywords:

transonic flow, airfoil, lift coefficient, supersonic region, shock wave

Downloads

Download data is not yet available.

Downloads

Published

2015-02-01

How to Cite

Babarykin, K. V. (2015). Transonic flow around the airfoil with aileron at a positive attack angle. Vestnik of Saint Petersburg University. Mathematics. Mechanics. Astronomy, 2(1), 84–90. Retrieved from https://math-mech-astr-journal.spbu.ru/article/view/11134

Issue

Vol. 2 No. 1 (2015)

Section

Mechanics

License

Articles of "Vestnik of Saint Petersburg University. Mathematics. Mechanics. Astronomy" are open access distributed under the terms of the License Agreement with Saint Petersburg State University, which permits to the authors unrestricted distribution and self-archiving free of charge.