This function determines a=[a1, a2, ...an] to solve the airfoil polynomial.
Zn=an(p)*X^(n-1/2), where n is the number of coordinates for the upper or
lower surface.
Input is a vector of PARSEC parameters p=[p1, p2, ...pn] where
p1=rle
p2=Xup
p3=Yup
p4=YXXup
p5=Xlow
p6=Ylow
p7=YXXlow
p8=yte
p9=delta yte (t.e. thickness)
p10=alpha te
p11=beta te
Information on the PARSEC airfoil parameterization is available at: http://www.as.dlr.de/hs/h-pdf/H141.pdf
引用格式
Sean Wu (2024). PARSEC airfoil polynomial coefficient solver (https://www.mathworks.com/matlabcentral/fileexchange/50138-parsec-airfoil-polynomial-coefficient-solver), MATLAB Central File Exchange. 检索来源 .
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- Industries > Aerospace and Defense > Airfoil tools >
- MATLAB > Mathematics > Elementary Math > Polynomials >
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致谢
启发作品: Airfoil optimization using Xfoil and PARSEC geometric parameterization, CB2: Airfoil Optimization with GUI
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