(1992) Experimental investigations of the vortex flow behind a circular cone at high angles of attack. Masters thesis, King Fahd University of Petroleum and Minerals.
|
PDF
9743.pdf Download (4MB) | Preview |
Arabic Abstract
-
English Abstract
The vortex flow which develops on a flying aircraft or missile becomes asymmetric at some large incidence. This asymmetric vortex configuration can give rise to significant undesirable side forces and yawing moments. The vortex-flow asymmetry was experimentally studied on a circular cone in the low-speed wind tunnel of KFUPM, at high angles of attack. Circumferential surface-pressure distributions were measured, at Re = 142,000 from a - 15 deg to 35 deg. Asymmetric pressure distribution due to vortex-flow asymmetry occurs on the lee-side, at a> 17 deg. Resulting in large side force. Inserting a longitudinal fm between the vortices at a = 25 deg and 35 deg appreciably reduces the asymmetry of the vortices and the side force. The angle of attack, a , at which the lee-side vortex system becomes asymmetric was determined, by smoke-flow visualization, as a function of free-stream Reynolds number Re, for Re = 5,000 to 202,000 (based on cone base diameter). The results show a clear dependence of a on Re and on surface conditions.
| Item Type: | Thesis (Masters) |
|---|---|
| Subjects: | Mechanical |
| Department: | College of Engineering and Physics > Mechanical Engineering |
| Committee Advisor: | Stahl, Wolfgang H. |
| Committee Members: | Hasan, M. A. Zaqir and El-Shaarawi, Maged A. I. |
| Depositing User: | Mr. Admin Admin |
| Date Deposited: | 22 Jun 2008 13:47 |
| Last Modified: | 01 Nov 2019 13:50 |
| URI: | http://eprints.kfupm.edu.sa/id/eprint/9743 |