Abstract
Some new developments relevant to the design of single-element airfoils using potential flow methods are presented. In particular, the ramifications of the unbounded trailing-edge pressure gradients generally present in the potential flow solution for the flow over an airfoil are examined, and the conditions necessary to obtain a class of airfoils having finite trailing-edge pressure gradients are developed. The incorporation of these conditions into the inverse method of Eppler for the design of low-speed airfoils is discussed, and a design generated using the modified scheme is presented for consideration. A detailed viscous analysis of this airfoil demonstrates a significant reduction in the strong viscous-inviscid interactions generally present near the trailing edge. These reductions offer the possibility of improved airfoil performance, as well as the possibility of improved accuracy in the methods of airfoil design and analysis.
| Original language | English (US) |
|---|---|
| Pages (from-to) | 97-103 |
| Number of pages | 7 |
| Journal | Journal of Aircraft |
| Volume | 23 |
| Issue number | 2 |
| DOIs | |
| State | Published - Jan 1 1986 |
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All Science Journal Classification (ASJC) codes
- Aerospace Engineering
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A class of airfoils having finite trailing-edge pressure gradients. / Ormsbee, A. I.; Maughmer, Mark David.
In: Journal of Aircraft, Vol. 23, No. 2, 01.01.1986, p. 97-103.Research output: Contribution to journal › Article
TY - JOUR
T1 - A class of airfoils having finite trailing-edge pressure gradients
AU - Ormsbee, A. I.
AU - Maughmer, Mark David
PY - 1986/1/1
Y1 - 1986/1/1
N2 - Some new developments relevant to the design of single-element airfoils using potential flow methods are presented. In particular, the ramifications of the unbounded trailing-edge pressure gradients generally present in the potential flow solution for the flow over an airfoil are examined, and the conditions necessary to obtain a class of airfoils having finite trailing-edge pressure gradients are developed. The incorporation of these conditions into the inverse method of Eppler for the design of low-speed airfoils is discussed, and a design generated using the modified scheme is presented for consideration. A detailed viscous analysis of this airfoil demonstrates a significant reduction in the strong viscous-inviscid interactions generally present near the trailing edge. These reductions offer the possibility of improved airfoil performance, as well as the possibility of improved accuracy in the methods of airfoil design and analysis.
AB - Some new developments relevant to the design of single-element airfoils using potential flow methods are presented. In particular, the ramifications of the unbounded trailing-edge pressure gradients generally present in the potential flow solution for the flow over an airfoil are examined, and the conditions necessary to obtain a class of airfoils having finite trailing-edge pressure gradients are developed. The incorporation of these conditions into the inverse method of Eppler for the design of low-speed airfoils is discussed, and a design generated using the modified scheme is presented for consideration. A detailed viscous analysis of this airfoil demonstrates a significant reduction in the strong viscous-inviscid interactions generally present near the trailing edge. These reductions offer the possibility of improved airfoil performance, as well as the possibility of improved accuracy in the methods of airfoil design and analysis.
UR - http://www.scopus.com/inward/record.url?scp=0022663870&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=0022663870&partnerID=8YFLogxK
U2 - 10.2514/3.56772
DO - 10.2514/3.56772
M3 - Article
AN - SCOPUS:0022663870
VL - 23
SP - 97
EP - 103
JO - Journal of Aircraft
JF - Journal of Aircraft
SN - 0021-8669
IS - 2
ER -