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Undeflected Common Research Model (uCRM): An Aerostructural Model for the Study of High Aspect Ratio Transport Aircraft Wings

TitleUndeflected Common Research Model (uCRM): An Aerostructural Model for the Study of High Aspect Ratio Transport Aircraft Wings
Publication TypeConference Papers
Year of Publication2017
AuthorsBrooks, TR, Kenway, GKW, Martins, JRRA
Conference Name18th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference
Date PublishedJune
Conference LocationDenver, CO

Since its introduction, the NASA Common Research Model (CRM) has served as a useful aerodynamic benchmark for CFD-based drag prediction and aerodynamic design optimization. The model was originally conceived as a purely aerodynamic benchmark and as such, the wing geometry corresponds to the deflected shape at the nominal 1 g flight condition. There has been growing interest in extending this model for aeroelastic studies. Due to its predefined deflection, the model is not suitable for aeroelastic analysis and design. To address this issue, we define an undeflected Common Research Model (uCRM), which includes the outer mold line geometry of the undeflected wing and the corresponding internal wingbox structure. The developed aeroelastic model achieves the flying shape of the CRM under the nominal flight condition. The topology of the wingbox is designed to be similar to that of a Boeing 777. The jig shape was obtained through an inverse design procedure where the objective was to minimize the difference between the 1 g aerostructurally deflected shape and the CRM. The original CRM has an aspect ratio of 9, so we refer to this model as the uCRM-9. Additionally, since modern transport aircraft are trending toward higher aspect ratio wing designs to reduce induced drag, and therefore fuel burn, there is a need for a higher aspect ratio variant of this model to assess next-generation wings. This variant, the uCRM-13.5, has a larger aspect ratio of 13.5 and is defined through a multipoint aerostructural optimization subject to buffet onset constraints. These models provide a publicly available benchmark for aeroelastic wing analysis and design optimization studies.

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