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Computational Fluid Dynamics Predictions of Control-Surface Effects for F-16XL Aircraft
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering.
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering.
2017 (English)In: Journal of Aircraft, ISSN 0021-8669, E-ISSN 1533-3868, Vol. 54, no 2, p. 395-408Article in journal (Refereed) Published
Abstract [en]

Computational fluid dynamics methods play an increasingly important role in aircraft design and development. Some examples are conditions that cannot be tested before a flight test. To rely on these methods, it is essential that they are assessed and evaluated with a state-of-the-art wind tunnel test and/or in-flight data. In a previous project, Cranked-Arrow Wing Aerodynamics Project International, it was reported that all computational fluid dynamics methods failed to some degree in the transonic regime where shock-vortex interaction phenomena were present. Detailed analysis of surface pressure distribution showed that computational fluid dynamics was not able replicate the correct flowfield and produce acceptable results. This paper aims to restudy those transonic flight conditions for which computational fluid dynamics underperforms and to try to determine or shed light on the extent to which surface effects contribute to the computational fluid dynamics predictions.

Place, publisher, year, edition, pages
AMER INST AERONAUTICS ASTRONAUTICS , 2017. Vol. 54, no 2, p. 395-408
National Category
Astronomy, Astrophysics and Cosmology
Identifiers
URN: urn:nbn:se:kth:diva-207717DOI: 10.2514/1.C033260ISI: 000399800100004OAI: oai:DiVA.org:kth-207717DiVA, id: diva2:1098489
Conference
52nd AIAA Aerospace Sciences Meeting, JAN 12-18, 2014, National Harbor, MD
Note

QC 20170524

Available from: 2017-05-24 Created: 2017-05-24 Last updated: 2017-05-24Bibliographically approved

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Rizzi, Arthur

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