An experimental and computational study of low Re number transitional flows over an aerofoil with leading edge slat

M Serdar Genc, Gary Lock, Unver Kaynak

Research output: Contribution to conferencePaper

6 Citations (Scopus)

Abstract

In this study, a multi-element aerofoil including NACA2415 aerofoil with NACA22 leading edge slat is experimentally and computationally investigated at a transitional Reynolds number of 2105. In the experiment, the single-element aerofoil experiences a laminar separation bubble, and a maximum lift coefficient of 1.3 at a stall angle of attack of 12. This flow has been numerically simulated by FLUENT, employing the recently developed, k-k L- and k- SST transition models. Both transition models are shown to accurately predict the location of the experimentally determined separation bubble. Experimental measurements illustrate that the leading-edge slat significantly delays the stall to an angle of attack of 20, with a maximum lift coefficient of 1.9. The fluid dynamics governing this improvement is the elimination of the separation bubble by the injection of high momentum fluid through the slat over the main aerofoil - an efficient means of flow control. Numerical simulations using the k-kL- transition model are shown to accurately predict the lift curve, including stall, but not the complete elimination of the separation bubble. Conversely, the lift curve prediction using the k- SST transition model is less successful, but the separation bubble is shown to fully vanish in agreement with the experiment.
Original languageEnglish
Publication statusPublished - 2008
Event8th AIAA Aviation Technology, Integration and Operations (ATIO) Conference, September 14, 2008 - September 19, 2008 - Anchorage, AK, USA United States
Duration: 14 Sep 200819 Sep 2008

Conference

Conference8th AIAA Aviation Technology, Integration and Operations (ATIO) Conference, September 14, 2008 - September 19, 2008
CountryUSA United States
CityAnchorage, AK
Period14/09/0819/09/08

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Airfoils
Angle of attack
Fluid dynamics
Flow control
Momentum
Reynolds number
Experiments
Fluids
Computer simulation

Cite this

Genc, M. S., Lock, G., & Kaynak, U. (2008). An experimental and computational study of low Re number transitional flows over an aerofoil with leading edge slat. Paper presented at 8th AIAA Aviation Technology, Integration and Operations (ATIO) Conference, September 14, 2008 - September 19, 2008, Anchorage, AK, USA United States.

An experimental and computational study of low Re number transitional flows over an aerofoil with leading edge slat. / Genc, M Serdar; Lock, Gary; Kaynak, Unver.

2008. Paper presented at 8th AIAA Aviation Technology, Integration and Operations (ATIO) Conference, September 14, 2008 - September 19, 2008, Anchorage, AK, USA United States.

Research output: Contribution to conferencePaper

Genc, MS, Lock, G & Kaynak, U 2008, 'An experimental and computational study of low Re number transitional flows over an aerofoil with leading edge slat' Paper presented at 8th AIAA Aviation Technology, Integration and Operations (ATIO) Conference, September 14, 2008 - September 19, 2008, Anchorage, AK, USA United States, 14/09/08 - 19/09/08, .
Genc MS, Lock G, Kaynak U. An experimental and computational study of low Re number transitional flows over an aerofoil with leading edge slat. 2008. Paper presented at 8th AIAA Aviation Technology, Integration and Operations (ATIO) Conference, September 14, 2008 - September 19, 2008, Anchorage, AK, USA United States.
Genc, M Serdar ; Lock, Gary ; Kaynak, Unver. / An experimental and computational study of low Re number transitional flows over an aerofoil with leading edge slat. Paper presented at 8th AIAA Aviation Technology, Integration and Operations (ATIO) Conference, September 14, 2008 - September 19, 2008, Anchorage, AK, USA United States.
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