Kama Şekilli Kanat Üzerindeki Süpersonik Akışı Çözmek için Sayısal Bir Algoritma

Bu makalede, kama şeklindeki bir kanat profili etrafındaki iki boyutlu süpersonik akışı çözmek için yeni bir algoritma geliştirilmiştir. Çözümü üretmek için MacCormack kestirici-düzeltici yönteminden fayda sağlanmıştır. Akış özelliklerini daha detaylı incelemek için C++ yazılım dilinde bir sayısal algoritma derlenmiş ve böylece ticari yazılımlar ile kıyas yapılması sağlanmıştır. Başlangıç şartları olarak serbest akım Mach sayısı 2 ve kama açısı 15º olacak şekilde geliştirilen algoritma derlenmiş ve çalıştırılmıştır. Derlenen programın açığa çıkardığı sonuç ile akış hızlarının sınırsız şekilde arttığı gözlemlenmiştir. Bu durumun düzeltilmesi ise algoritmaya suni dağılım terimi eklenerek yapılmıştır. Suni dağılım teriminin geliştirilen koda eklenmesi ile sonuç istikrarlı olmuş ve beklenen şokun gözlemlenmesine neden olmuştur. Aynı durum ayrıca ANSYS Fluent ve CFL3D yazılımları ile ikinci derecede kesikli hale getirilerek de simüle edilmiştir.

A Numerical Algorithm to Solve Supersonic Flow over a Wedge Shaped Airfoil

In this paper, a new algorithm is developed to solve a two dimensional supersonic flow around a wedge-shaped airfoil. The MacCormackpredictor-corrector method is utilized to develop a solution. To further investigate the flow properties, a numerical algorithm written inC++ has been compiled so that it may be compared to commercial softwares. The developed algorithm is compiled and run with theinitial conditions of a free stream Mach number of 2 while the wedge angle is set at 15º. The compiled program revealed that the flowvelocities increased without bound. Adjustment of this condition was achieved by adding artificial dissipation. The addition ofdissipation term into the code resulted stable output and the presence of a shock. Same case was also simulated with ANSYS Fluentand CFL3D softwares using second order discretization.

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