TY  - JOUR
TT  - Airfoil Optimization for Level Flight
AU  - Körpe, Sinan
AU  - Darak, Hakan
PY  - 2017
DA  - December
Y2  - 2017
DO  - 10.30518/jav.346425
JF  - Journal of Aviation
JO  - JAV
PB  - Vedat Veli ÇAY
WT  - DergiPark
SN  - 2587-1676
SP  - 107
EP  - 119
VL  - 1
IS  - 2
KW  - Eniyileme
KW  - Ardışık İkinci Derece Programlama
KW  - Xfoil
KW  - MATLAB
KW  - Kanat profili
N2  - In this study, theoptimization problems that are based on CL and CD values,which are obtained by a fast aerodynamic solver consisting of three dimensionalpanel method and one-way two dimensional boundary layer solver, are solved forfour different speed values in level flight. These values are stall speed, the highestrange speed, the highest endurance speed and the maximum speed. In order tosolve the optimization problems, the combination of MATLAB program and Xfoilprogram has been provided. Lift and drag force coefficients are calculated inXfoil program for the Jacobian matrix of the constraints and the gradientvector of the objective function that are required by the sequential quadraticprogramming method in MATLAB. In the first phase, minimization the drag coefficientat the determined angle of attack is defined as the objective function whilethe lift coefficient at that angle of attack is defined as the equalityconstraint. In the second phase, in addition to the above defined problem, thelift coefficient provided by the airfoil at the stall angle of attack isdefined as the equality problem and the optimization problems are solved.
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[2]	Garcia, M.J. , Boulanger, P. , Giraldo, S. “CFD Based Wing Shape Optimization Through Gradient-Based Method” EngOpt 2008 - International Conference on Engineering Optimization Rio de Janeiro, Brazil, 01 - 05 June 2008
[3]	NACA 4 Hane hesaplama yöntemi, Erişim tarihi: 29.12.2016 http://airfoiltools.com/airfoil/naca4digit
[4]	Everstine, G.C. (2010) Numerical Solution of Partial Differential Equations Erişim Tarihi: 05.01.2016 http://gwu.geverstine.com/pdenum.pdf
[5]	Körpe, S.D. ve Özgen S (2016) “Morphing Wing Optimization for Steady Level Flight” Proc IMechE Part G: J Aerospace Engineering 
DOI: 10.1177/0954410016662063
[6]	Darak, H “Düz Uçuş için Kanat Profili Eniyilemesi” Yüksek lisans tezi, Türk Hava Kurumu Üniversitesi, 2017. 
[7]	Edelman, L. XFoil-MATLAB ortak  arayüzü Erişim Tarihi: 10.11.2016
	https://www.mathworks.com/matlabcentral/fileexchange/49706-xfoil-interface-updated
UR  - https://doi.org/10.30518/jav.346425
L1  - https://dergipark.org.tr/en/download/article-file/386305
ER  -