Open AccessExperimental and computational analysis of stall cells on rectangular wings
Author(s) -
Manolesos Marinos,
Papadakis Georgios,
Voutsinas Spyros G.
Publication year - 2014
Publication title -
wind energy
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 0.743
H-Index - 92
eISSN - 1099-1824
pISSN - 1095-4244
DOI - 10.1002/we.1609
Subject(s) - wake , stall (fluid mechanics) , vortex , mechanics , reynolds averaged navier–stokes equations , reynolds number , angle of attack , wing , physics , lift (data mining) , aerodynamics , geometry , vortex lift , airfoil , drag , lift to drag ratio , vortex shedding , trailing edge , computational fluid dynamics , lift coefficient , aerospace engineering , mathematics , engineering , computer science , turbulence , data mining
The present paper is the second part of a combined (experimental and computational) study on stall cells (SCs) on a rectangular wing. In the first part, tuft data were used in order to geometrically characterize a stabilized SC resulting from a localized spanwise disturbance introduced by a zigzag tape. Here, pressure measurements on the model and in the wake and aerodynamic polars at midspan are reported. The wing model had an aspect ratio value of 2, the Reynolds number was 10 6 and the range of angles of attack ( α ) was from −6 ° to 16 ° . Experimental results confirm previous findings. Furthermore, two‐dimensional and three‐dimensional Reynolds Averaged Navier‐Stokes RANS simulations are used in order to better understand the structure of SCs. 3D simulations reproduce the experimental data with a 3° delay in α and permit a qualitative analysis. It is found that the SC vortices start normal to the wing surface and extend downstream in the wake; the evolution of the SC vortices in the wake is in strong interaction with the separation line vortex and the trailing edge line vortex; as the SC vortex develops downstream in the wake, its centreline is contracted towards the SC centre; the wing wake is pushed upstream at the centre of the SC and downstream at the sides by the SC vortices; spanwise lift and drag distributions always attain their minimum at the SC centre. Copyright © 2013 John Wiley & Sons, Ltd.