An Analysis and Design Framework for Extensive Natural Laminar Flow of Aircraft Wings

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The objective of this collaborative project is to develop the necessary algorithms and tools for the analysis and design of extended region of laminar flow over aircraft components via aerodynamic shape optimization. The framework will employ a Reynolds-averaged Navier-Stokes solver, and turbulence and correlation-based transition models to accurately predict the transition point and an adjoint-based design optimization approach to perform both shape and planform optimization. The ultimate objective is to develop the enabling technologies to design environmentally responsible aircraft. This project will contribute towards the development of advanced aircraft concepts that satisfy the N+3 (2025) or equivalent EU standards. Modern aircraft design involves a large number of design variables for a multitude of disciplines culminating in extremely large number of data sets. Obtaining high fidelity solutions for all combinations of such parameters is currently computationally intractable. To alleviate this issue, designers often rely on surrogate models to simulate the input-output behaviour of complex systems based on large data sets in order to obtain a continuous approximation of functions of interest across the parameter space. In summary, the collaborative research and development will develop the necessary novel algorithms through three objectives. Objective One, implement, verify, and validate a transition model for a RANS-based solver with crossflow models. Objective Two, develop a design framework for natural laminar flow and investigate sensitivity of transitional flow to external perturbations through uncertainty quantification. Objective Three, develop a novel adaptive derivative-enhanced surrogate model of large data sets for performance and load analysis.