Aerodynamic assessment of sub-scale aircraft model

A multi-fidelity approach

Master thesis (2022)

Authors

A.U.M. Baliga Aerospace Engineering

Contributors

G. la Rocca Flight Performance and Propulsion - Aerospace Engineering (supervisor 1)
Faculty
Aerospace Engineering
Copyright: © 2022 Adithya Baliga
RANS Multi-fidelity 3D Panel Method Computational Scaling Sub-scale Aircraft Model Design
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Published Date

30-09-2022

Language

English

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Faculty

Aerospace Engineering

Abstract

Novel designs like the Flying-V, Prandtl-Plane and Blended Wing-Body show promise towards sustainable aviation. In the preliminary design phase, Sub-scale Flight Test (SFT) is a reliable method to get insight into the flight behavior of these designs. The effectiveness and value provided by SFT depends on the similitude between the SFT model and the full-scale aircraft. The method of
computational scaling is a state-of-the-art method into designing SFT models, that maximizes the similitude. However, this method is often infeasible because of large computational costs. Of the various analyses in this methodology, the aerodynamic analysis is computationally most expensive. Therefore, this research developed a multi-fidelity approach for the assessment of aerodynamic
characteristics of SFT model. The approach utilized a blend of Reynolds- Averaged Navier-Stokes (RANS) and 3D-Panel Method (3DPM). This provided a good tradeoff between accuracy and computational cost, making the method of computational scaling a feasible method into design of SFT models.