A computational study of a close-coupled delta canard-wing-body configuration

Date

1996-06-20

Author

Tuncer, İsmail Hakkı
Vandyken, Robert B

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Subsonic flowfields over a close-coupled delta canard-wing-body configuration at high angles of attack from 20° to 30' are computed using the OVERFLOW Navier-Stokes solver. Computed flowfields are presented in terms of particle traces, surface streamlines and leeward-side surface pressure distributions for the canard on and off configurations. The interaction between the canard and the wing vortices, wing vortex breakdown and the influence of the canard on vortex breakdown are identified. It is computed that the presence of the canard delays the wing vortex breakdown to positions aft, of the wing trailing edge at α = 20' and n = 24.2'. The surface pressure distributions on the wing, canard and fuselage compare well with the experimental data at α = 20'. As the angle of attack increases, some discrepancies in the vortex trajectories are observed.

Subject Keywords

Aerodynamics, Angle of attack, Flow fields, Navier Stokes equations, Pressure distribution, Vortex flow

URI

https://hdl.handle.net/11511/72338
https://www.scopus.com/record/display.uri?eid=2-s2.0-84964267068&origin=resultslist&sort=plf-f&src=s&st1=&st2=&sid=6c53f74944f55fd7782b8ac1211f8eaa&sot=b&sdt=b&sl=93&s=TITLE-ABS-KEY+%28A+computational+study+of+a+close-coupled+delta+canard-wing-body+configuration%29&relpos=1&citeCnt=5&searchTerm=

Conference Name

AIAA 14th Applied Aerodynamics Conference (20 - 24 Haziran 1996)

Collections

Department of Aerospace Engineering, Conference / Seminar

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Citation Formats

İ. H. Tuncer and R. B. Vandyken, “A computational study of a close-coupled delta canard-wing-body configuration,” New Orleans, USA, 1996, p. 498, Accessed: 00, 2021. [Online]. Available: https://hdl.handle.net/11511/72338.