Multidisciplinary design optimization of transonic wings with boundary layer suction

Abstract

A quasi-three-dimensional aerodynamic solver is developed for aerodynamic analysis of wings in a transonic regime, able to capture the effect of Boundary Layer Suction (BLS) in Hybrid Laminar Flow Control (HLFC) application or transition to turbulent flow for Natural Laminar Flow (NLF). The tool provides accurate results but without the high computational cost of high-fidelity tools. The solver combines the use of an Euler flow solver characterized by an integral boundary layer method and Linear Stability Analysis using a 2.75D approximation for transition prediction. In particular, a conical transformation is adopted, including the determination of the shock-wave position. The solver is implemented in a Multidisciplinary Design Optimization (MDO) framework, including wing weights estimation and aircraft performance analysis. The framework consists of different modules: aerodynamics, structure, suction system analysis, and performance evaluation. Using a genetic algorithm and considering HLFC technology, wing MDO has been performed to find the optimum wing planform and airfoil shape. A backward swept wing aircraft, developed inside the Cluster of Excellence SE²A (Sustainable and Energy Efficient Aviation) is studied. Novel technologies such as active flow control, limited maximum load factor due to load alleviation and novel materials allow a fuel weight reduction of 6%.

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