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Experimental results of the control of a vortical flow by tangential blowingThe results of a wind tunnel test to investigate the controlling effects of tangential, leading edge blowing on the vortical flow over a delta wing are given. Blowing is used to directly control the crossflow separation points at the rounded leading edge and hence, the trajectory of the feeding sheet and the location of the vortex. Experiments were conducted for both co-flowing and counter-flowing configurations over a range of angles of attack from 0 to 90 degrees. Results in the form of pressure distributions, overall force coefficients and flow mappings were obtained. The emphasis is on data presentation rather than detailed analysis. The initial results indicate that the co-flowing configuration was capable of extending the regime of stable, controlled vortical flow over the upper surface by approximately 30 degrees angle of attack for modest blowing requirements. Increases in maximum normal force coefficient of approximately 30% were achieved and significant rolling moments produced at angles of attack from 30 to 60 degrees. The counter-flowing configuration indicated only minor lift augmentation with the exception of an isolated occurrence at 20 degrees angle of attack. At that condition, with very weak blowing, a lift augmentation of approximately 20 was measured.
Document ID
19860020622
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Wood, N. J.
(Stanford Univ. CA, United States)
Roberts, L.
(Stanford Univ. CA, United States)
Date Acquired
September 5, 2013
Publication Date
May 1, 1986
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
JIAA-TR-71
NASA-CR-176932
NAS 1.26:176932
Accession Number
86N30094
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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