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Euler technology assessment for preliminary aircraft design employing OVERFLOW code with multiblock structured-grid methodThe viability of applying a state-of-the-art Euler code to calculate the aerodynamic forces and moments through maximum lift coefficient for a generic sharp-edge configuration is assessed. The OVERFLOW code, a method employing overset (Chimera) grids, was used to conduct mesh refinement studies, a wind-tunnel wall sensitivity study, and a 22-run computational matrix of flow conditions, including sideslip runs and geometry variations. The subject configuration was a generic wing-body-tail geometry with chined forebody, swept wing leading-edge, and deflected part-span leading-edge flap. The analysis showed that the Euler method is adequate for capturing some of the non-linear aerodynamic effects resulting from leading-edge and forebody vortices produced at high angle-of-attack through C(sub Lmax). Computed forces and moments, as well as surface pressures, match well enough useful preliminary design information to be extracted. Vortex burst effects and vortex interactions with the configuration are also investigated.
Document ID
19950016678
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Treiber, David A. (Boeing Defense and Space Group Seattle, WA, United States)
Muilenburg, Dennis A. (Boeing Defense and Space Group Seattle, WA, United States)
Date Acquired
September 6, 2013
Publication Date
March 1, 1995
Publication Information
Publisher: NASA
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-4651
NAS 1.26:4651
Accession Number
95N23095
Funding Number(s)
CONTRACT_GRANT: NAS1-18762
PROJECT: RTOP 505-68-30-03
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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