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Studies of vortex flaps for different sweepback angle delta wings

Published online by Cambridge University Press:  04 July 2016

K. Rinoie
K. Rinoie*
Affiliation:
Department of Aeronautics and AstronauticsUniversity of TokyoTokyo, Japan
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Abstract

Low speed windtunnel measurements were made on a 50° delta wing with leading edge vortex flaps. Improvements in the lift/drag ratio were obtained by deflecting the leading edge vortex flap. Comparisons were made between the previously measured 60° and 70° delta wing results and the present 50° wing results. Improvements in the lift/drag ratio of the 50° delta wing were attained over a wider lift coefficient range than for the 70° delta wing. The highest lift/drag ratio for the 50° delta wing is achieved when the flow attaches to the flap surface without any large area of separation. Estimations of the aerodynamic forces were also made using a quasi-vortex lattice method coupled with the leading edge suction analogy for the 50°, 60° and 70° delta wings. The results obtained from this analysis agree qualitatively with the experimental results.

Type
Research Article
Information
The Aeronautical Journal , Volume 101 , Issue 1009 , November 1997 , pp. 409 - 416
Copyright
Copyright © Royal Aeronautical Society 1997 

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