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An experimental investigation of three dimensional low speed minimum interference wind tunnel for high lift wingsAs a means to achieve a minimum interference correction wind tunnel, a partially actively controlled test section was experimentally examined. A jet flapped wing with 0.91 m (36 in) span and R = 4.05 was used as a model to create moderately high lift coefficients. The partially controlled test section was simulated using an insert, a rectangular box 0.96 x 1.44 m (3.14 x 4.71 ft) open on both ends in the direction of the tunnel air flow, placed in the University of Washington Aeronautical Laboratories (UWAL) 2.44 x 3.66 m (8 x 12 ft) wind tunnel. A tail located three chords behind the wing was used to measure the downwash at the tail region. The experimental data indicates that, within the range of momentum coefficient examined, it appears to be unnecessary to actively control all four sides of the test section walls in order to achieve the near interference free flow field environment in a small wind tunnel. The remaining wall interference can be satisfactorily corrected by the vortex lattice method.
Document ID
19810016502
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Shindo, S. (Washington Univ. Seattle, WA, United States)
Joppa, R. G. (Washington Univ. Seattle, WA, United States)
Date Acquired
September 4, 2013
Publication Date
September 1, 1980
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-164439
Accession Number
81N25037
Funding Number(s)
CONTRACT_GRANT: NSG-2260
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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