NDLI: An experimental investigation of three dimensional low speed minimum interference wind tunnel for high lift wings

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An experimental investigation of three dimensional low speed minimum interference wind tunnel for high lift wings

Content Provider	NASA Technical Reports Server (NTRS)
Author	Joppa, R. G. Shindo, S.
Copyright Year	1980
Description	As 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.
File Size	2908733
Page Count	26
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19810016502
Archival Resource Key	ark:/13960/t0tr0qh5n
Language	English
Publisher Date	1980-09-01
Access Restriction	Open
Subject Keyword	Aerodynamics Wind Tunnels Wind Tunnel Walls Lift Simulation Vortices Vortex Lattice Method Flaps Control Surfaces Investigation Experimentation Interference Lift Wing Flaps Aerodynamic Characteristics Interference Drag Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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