The aeroelastic response of a NACA 0012 airfoil with freedom to move in pitch only, and forced to oscillate through dynamic stall in subsonic flow is simulated numerically using a finite difference method. The unsteady aerodynamic pitching moment is obtained via a semi-empirical dynamic stall model;
Dynamically determining force functions for non-linear oscillators
โ Scribed by David K. Arrowsmith
- Publisher
- Springer Netherlands
- Year
- 1984
- Tongue
- English
- Weight
- 382 KB
- Volume
- 19
- Category
- Article
- ISSN
- 0025-6455
No coin nor oath required. For personal study only.
๐ SIMILAR VOLUMES
A non-linear scales method is presented for the analysis of strongly non-linear oscillators of the form Y: + g(x) = ef (x, d:), where g(x) is an arbitrary non-linear function of the displacement x. We assumed that x(t,~) x0(~,,7) + m-, m T~ = ~,~=~ e'~xn(~) + O(e'~), where d~/dt = ~,~=1 e'~R~(~) , d
The response of a non-linear oscillator of the form xยจ+ f(A, B, x) = og (E, m, w, k, t), where f(A, B, x) is an odd non-linearity and o is small, for A Q 0 and B q 0 is considered. The homoclinic orbits for the unperturbed system are obtained by using Jacobian elliptic functions with the generalized