Applied Mathematics and Mechanics

, Volume 20, Issue 8, pp 895–907

# Research on the hysteresis properties of unsteady aerodynamics about the oscillating wings

• Gao Zhenghong
Article

## Abstract

In the work, it is shown the numerical investigations about the unsteady inviscid results obtained for the pitching oscillating wings at different angles of attack. The results are obtained by solving the unsteady Euler equations in a bodyfitted coordinate system. It is based on the four-stage runge-Kutta time stepping scheme. Meanwhile to increase the time step that is limited by Courant limit (CFL), the implicit residual smoothing with local variable parameters is used. As a result, the unsteady aerodynamics about a rectangular wing and a delta wing, which are oscillated in pitching with different frequencies, are shown in this paper. The properties of the unsteady aerodynamics in these cases are researched here.

## Key words

unsteady flow hysteresis high angle of attach vortical flow

O355 V211.41

## References

1. [1]
Robinson M R, Herbst W B. The X-31 advanced highly maneuverable aircaft[A]. In:ICAS 90-0.4[C], 1990, 28–36.Google Scholar
2. [2]
Borland C. Numerical solution of three-D unsteady transonic flow over swept wing [R]. AIAA paper 80–1369, 1980.Google Scholar
3. [3]
Gad-el-Hak M, Ho C-M. The pitching delta wing[J].AIAA Journal, 1985,23(11): 1160–1165.
4. [4]
Jameson A, Schmidt W, Turkel E. Numerical solutions of the Euler equations by finite volume methods using Runge-Kutta time stepping scheme[R]. AIAA paper 81-1259, 1981.Google Scholar
5. [5]
Gao Zhenghong. Unconditional stable solutions of Euler equations for two- and three-D wings in arbitrary motion[J].Applied Mathematics and Mechanics (English Ed). 1995,16(12): 1209–1220.
6. [6]
Gao Zhenghong. Unconditional stable solutions of unsteady Euler equations for rigid and flexible oscillating airfoils [A]. In:FLM-94/18Lehrstulh fur Fluidmechanik, TU Muenchen Deutschland[C], 1994, 1–20. (in Germany).Google Scholar