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Predictions of stability and control for a flying wing
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Marcus Wallenberg Laboratory MWL.
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering.
2014 (English)In: Aerospace Science and Technology, ISSN 1270-9638, E-ISSN 1626-3219, Vol. 39, 179-186 p.Article in journal (Refereed) Published
Abstract [en]

The numerical simulation of a generic reduced radar signature tailless aircraft is considered. Investigation compares simulated data to low-speed wind tunnel experiments. Focus is on numerical predictions of steady longitudinal and lateral aerodynamics and influence of control surfaces on aerodynamic forces. Fully turbulent and transitional Reynolds Averaged Navier-Stokes (RANS) simulations predicted in agreement with experiment unstable pitch characteristics for low angles of attack (alpha), this was not the case for inviscid or laminar simulations. However, all simulations captured a sudden rapid increase in nose up pitch moment at higher angles of attack compared to experiments. Time accurate computations (URANS) captured non-linearity and unsteadiness in yaw moment with respect to differential split flap deflections for the studied angles of attack.

Place, publisher, year, edition, pages
2014. Vol. 39, 179-186 p.
Keyword [en]
UCAV, Computational fluid dynamics, Aerodynamics, Stability and control
National Category
Aerospace Engineering
Identifiers
URN: urn:nbn:se:kth:diva-160411DOI: 10.1016/j.ast.2014.09.007ISI: 000347743100018Scopus ID: 2-s2.0-84907936526OAI: oai:DiVA.org:kth-160411DiVA: diva2:790347
Note

QC 20150224

Available from: 2015-02-24 Created: 2015-02-19 Last updated: 2017-12-04Bibliographically approved

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