ONERA M6 kanadının belirsizlik altında şekil optimizasyonu ile tasarımı

Öz

Aerodinamik şekil optimizasyon süreçleri, tekli veya çoklu tasarım hedeflerini sağlayan kompleks problemler için sıklıkla kullanılmaktadır. Geleneksel ve belirsizliğin dahil edilmediği problemlere nazaran belirsizliklerin dahil edildiği ve yüksek değişken sayısına sahip sağlam optimizasyon yöntemlerinin hesaplama yükü oldukça yüksektir. Bu problemin önüne geçmek için, bu çalışmada, temel bileşenler analizi, tümevarımsal tasarım araştırma yöntemi ile entegre edilerek ONERA M6 kanadının sağlam şekil optimizasyonu gerçekleştirilmiştir. Temel bileşenler analizi yöntemi, kanat geometrisinin tasarım değişkeni sayısını azaltmak için tercih edilmiştir. Hesaplamalı akışkanlar dinamiği analizi kullanımı sonucunda ortaya çıkan yüksek çözüm süreleri ise, temel bileşenler analizi yönteminin bir vekil model tekniği olan radyal bazlı fonksiyon ile birlikte kullanılmasıyla oluşturulan bir veri tahmin modeli ile azaltılmıştır. Transonik akış rejimi için Mach sayısındaki belirsizlikler, önerilen tümevarımsal tasarım araştırma yöntemi tabanlı yönteme dahil edilerek sağlam optimizasyon gerçekleştirilmiştir. Sağlam tasarımların performans tahminlerinin hesaplamalı akışkanlar dinamiği analiz sonuçlarına oldukça yakın elde edilmesi, önerilen yöntemin etkinliğini göstermiştir.

Anahtar Kelimeler

• Hesaplamalı akışkanlar dinamiği
• temel bileşenler analizi
• belirsizlik
• sağlam optimizasyon

Design of the ONERA M6 wing by shape optimization under uncertainty

Öz

Aerodynamic shape optimization processes are often used for complex problems that meet single or multi-objective design requirements. The robust aerodynamic shape optimization techniques with a high number of design variables that consider uncertainties have a huge computational burden compared to the traditional aerodynamic shape optimization techniques without considering uncertainties. To overcome this issue, in this study, the proper orthogonal decomposition is integrated with the inductive design exploration method to use for the robust shape optimization of the ONERA M6 wing. The proper orthogonal decomposition method is utilized for reducing the number of design variables of the wing geometry. The cost due to the computational fluid dynamics analysis is mitigated by incorporating the proper orthogonal decomposition with a surrogate modeling technique called the radial basis function. The robust optimization is conducted by the proposed approach based on the inductive design exploration method by accounting for uncertainties of the Mach number in the transonic flow regime. The agreement between the performance predictions of the robust designs and the computational fluid dynamics analysis results showed the effectiveness of the proposed approach.

Anahtar Kelimeler

• Computational fluid dynamics
• proper orthogonal decomposition
• uncertainty
• robust optimization

Kaynakça

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