B1.6 - Effective Design Methods and Design Exploration for Laminar Wing and Fuselage

This project pursues design and design exploration of flow laminarity on highly swept wings with the ambition to formulate a robust design methodology accounting for uncertainties. RANS simulations with correlation-based transition transport models for 3D flows are employed and applied together with surrogate models for computational efficiency. This project builds upon previous research within the SE2A Cluster that optimized NLF, HLFC wings  under subsonic and transonic flight conditions using a multi-fidelity approach, advanced transition methods, efficient optimization and uncertainty quantification.

Research objectives

• Devise multi-fidelity strategies for wing design to optimize for global minimum drag with feasible design parameterizations and constraints for NLF as well as HLFC. (Optimization)
• Rigorous assessment of different uncertainties and their influence on key performance indicators such as drag or energy consumption (Uncertainty Quantification)
• Incorporate improved and validated correlation-based transition transport models into the design workflows and uncertainty investigations. (Accurate flow physics)
• Employ surrogate models to obtain a computationally efficient design based on wing optimization under uncertainties. (Robust optimization)

Publications

• Parekh, J.; Bekemeyer, P.; et al. (2023): Laminar Airfoil Design under Uncertainties using the DLR Gamma Transition Model. Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V.. (Text). doi.org/10.25967/610225.