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a cfd database for airfoils and wings at post-stall angles of attackThis paper presents selected results from an ongoing effort to develop an aerodynamic database from Reynolds-Averaged Navier-Stokes (RANS) computational analysis of airfoils and wings at stall and post-stall angles of attack. The data obtained from this effort will be used for validation and refinement of a low-order post-stall prediction method developed at NCSU, and to fill existing gaps in high angle of attack data in the literature. Such data could have potential applications in post-stall flight dynamics, helicopter aerodynamics and wind turbine aerodynamics. An overview of the NASA TetrUSS CFD package used for the RANS computational approach is presented. Detailed results for three airfoils are presented to compare their stall and post-stall behavior. The results for finite wings at stall and post-stall conditions focus on the effects of taper-ratio and sweep angle, with particular attention to whether the sectional flows can be approximated using two-dimensional flow over a stalled airfoil. While this approximation seems reasonable for unswept wings even at post-stall conditions, significant spanwise flow on stalled swept wings preclude the use of two-dimensional data to model sectional flows on swept wings. Thus, further effort is needed in low-order aerodynamic modeling of swept wings at stalled conditions.
Document ID
20140000500
Document Type
Conference Paper
Authors
Petrilli, Justin
(North Carolina State Univ. Raleigh, NC, United States)
Paul, Ryan
(North Carolina State Univ. Raleigh, NC, United States)
Gopalarathnam, Ashok
(North Carolina State Univ. Raleigh, NC, United States)
Frink, Neal T.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
January 31, 2014
Publication Date
June 24, 2013
Subject Category
Aerodynamics
Report/Patent Number
NF1676L-16579
Meeting Information
AIAA Applied Aerodynamics Conference(San Diego, CA)
Funding Number(s)
WBS: WBS 284848.02.05.07.01
Distribution Limits
Public
Copyright
Public Use Permitted.

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