Effects of wing geometry on wing-body-tail interference in subsonic flow

Davari, A. R ; Sharif University of Technology

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  1. Type of Document: Article
  2. DOI: 10.1016/j.scient.2011.05.031
  3. Abstract:
  4. Extensive wind tunnel tests were performed on several wing- body-tail combinations in subsonic flow to study the effects of wing geometric parameters on the flow field over the tail. For each configuration, tail surface pressure distribution, as well as the velocity contour at a plane perpendicular to the flow direction behind the wing was measured. The results show a strong effect of wing to tail span ratio, as well as wing aspect ratio, on the flowfield downstream of the wing. For low sweep wings, as those considered here, wing and body interference effects on the tail are associated with the wing tip vortex and nose-body vortex
  5. Keywords:
  6. Forebody vortex shedding ; Interference ; Tip vortex ; A-plane ; Flow direction ; Geometric parameter ; Interference effects ; Span ratios ; Surface pressure distribution ; Sweep wings ; Velocity contours ; Wind tunnel tests ; Wing aspect ratio ; Wing geometry ; Wingtip vortex ; Aerodynamics ; Aspect ratio ; Flow fields ; Vortex flow ; Wind tunnels ; Subsonic flow ; Flow field ; Geometry ; Vortex ; Wind tunnel
  7. Source: Scientia Iranica ; Volume 18, Issue 3 B , 2011 , Pages 407-415 ; 10263098 (ISSN)
  8. URL: http://www.sciencedirect.com/science/article/pii/S1026309811000964