High-Fidelity Aerodynamic Shape Optimization of a Lifting-Fuselage Concept for Regional Aircraft. Reist, T. A. & Zingg, D. W. Journal of Aircraft, 54(3):1085–1097, October, 2017. doi abstract bibtex High-fidelity aerodynamic shape optimization based on the Reynolds-averaged Navier–Stokes equations is used to optimize the aerodynamic performance of a conventional tube-and-wing design, a hybrid wing-body, and a novel lifting-fuselage concept for regional-class aircraft. Trim-constrained drag minimization is performed on a hybrid wing-body design, with an optimized conventional design serving as a performance reference. The optimized regional-class hybrid wing-body yields no drag savings when compared with the conventional reference aircraft. Starting from the optimized hybrid wing-body, an exploratory optimization with significant geometric freedom is then performed, resulting in a novel shape with a slender lifting fuselage and distinct wings. Based on this exploratory result, a new regional-class lifting-fuselage configuration is designed and optimized. With a span constrained by code ``C'' gate limits and having the same wing-only span as the conventional reference aircraft, this new design produces up to 10% lower drag than the reference aircraft. The effect of structural weight uncertainties, cruise altitude, and stability requirements are also examined.
@Article{Reist2017,
author = {Reist, Thomas A. and Zingg, David W.},
title = {High-Fidelity Aerodynamic Shape Optimization of a Lifting-Fuselage Concept for Regional Aircraft},
doi = {10.2514/1.C033798},
journal = {Journal of Aircraft},
month = {October},
number = {3},
pages = {1085--1097},
volume = {54},
year = {2017},
abstract = { High-fidelity aerodynamic shape optimization based on the Reynolds-averaged Navier--Stokes equations is used to optimize the aerodynamic performance of a conventional tube-and-wing design, a hybrid wing-body, and a novel lifting-fuselage concept for regional-class aircraft. Trim-constrained drag minimization is performed on a hybrid wing-body design, with an optimized conventional design serving as a performance reference. The optimized regional-class hybrid wing-body yields no drag savings when compared with the conventional reference aircraft. Starting from the optimized hybrid wing-body, an exploratory optimization with significant geometric freedom is then performed, resulting in a novel shape with a slender lifting fuselage and distinct wings. Based on this exploratory result, a new regional-class lifting-fuselage configuration is designed and optimized. With a span constrained by code ``C'' gate limits and having the same wing-only span as the conventional
reference aircraft, this new design produces up to 10\% lower drag than the reference aircraft. The effect of structural weight uncertainties, cruise altitude, and stability requirements are also examined.}
}
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