This content is not included in
your SAE MOBILUS subscription, or you are not logged in.
Investigation of Dynamic Roughness Flow Control on NACA 0012 Airfoil at Low Reynolds Number
Technical Paper
2013-01-2096
ISSN: 0148-7191, e-ISSN: 2688-3627
Annotation ability available
Sector:
Language:
English
Abstract
There is an ever growing need in the aircraft industry to increase the performance of a flight vehicle. To enhance performance of the flight vehicle one active area of research effort has been focused on the control of the boundary layer by both active and passive means. An effective flow control mechanism can improve the performance of a flight vehicle by eliminating boundary layer separation at the leading edge (as long as the energy required to drive the mechanism is not greater than the savings). In this paper the effectiveness of a novel active flow control technique known as dynamic roughness (DR) to eliminate flow separation in a stalled NACA 0012 wing has been explored. As opposed to static roughness, dynamic roughness utilizes small time-dependent deforming elements or humps with amplitudes that are on the order of the local boundary layer height to energize the local boundary layer. DR is primarily characterized by the maximum amplitude and operating frequency. A flow visualization study was conducted on a NACA 0012 wing at an angle of attack of 13° and Reynolds numbers of 25,000 and 50,000 at fixed maximum DR amplitude and varying frequencies. The study suggests that DR is an effective method of reattaching a totally separated boundary layer. For our flow we discovered that a threshold frequency exists for DR to be effective.
Authors
Citation
Jakkali, V., Huebsch, W., Robert, A., Hamburg, S. et al., "Investigation of Dynamic Roughness Flow Control on NACA 0012 Airfoil at Low Reynolds Number," SAE Technical Paper 2013-01-2096, 2013, https://doi.org/10.4271/2013-01-2096.Also In
References
- Rinoie , K. and Takemura , N. Oscillating behavior of laminar separation bubble formed on an airfoil near stall The Aeronautical Journal March 2004 153 163
- Greenblatt , D. and Wygnanski , I. The Control of Flow Separation by Periodic Excitation Progress in Aerospace Sciences Elsevier Pergamon New York 2000 487 545
- Bushnell , D. , and Hefner , J. Effect of Compliant Wall Motion on Turbulent Boundary Layers Physics of Fluids 20 10 1977 S31 S48 10.1063/1.861756
- Lekoudis , S. G. and Sengupta , T. K. Two- Dimensional Turbulent Boundary Layers Over Rigid and Moving Swept Wavy Surfaces Physics of Fluids 29 4 April 1986 964 970 10.1063/1.865691
- Huebsch , W.W. , Gall , P.D. , Hamburg , S.D. , Rothmayer , A.P. Dynamic roughness as a means of leading edge separation flow control AIAA Journal of Aircraft 49 1 2012 108 115 10.2514/1.C031350
- Grager , T. , Rothmayer , A. , Huebsch , W. and Hu , H. Low Reynolds Number Stall Suppression with Dynamic Roughness AIAA 2012-2681, 6th AIAA Flow Control Conference 2012
- Gall , P. D. , Huebsch , W. and Rothmayer , A. Dynamic Roughness as a Means of Leading Edge Separtaion Flow Control 27 th International Congress of the Aeronautical Sciences
- Huebsch , W.W. Two-Dimensional Simulation of Dynamic Surface Roughness for Aerodynamic Flow Control AIAA Journal of Aircraft 43 2 2006 353 362 10.2514/1.14708