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Turbulent Navier-Stokes Flow Analysis of an Advanced Semispan Diamond-Wing Model in Tunnel and Free Air at High-Lift ConditionsTurbulent Navier-Stokes computational results are presented for an advanced diamond wing semispan model at low-speed, high-lift conditions. The numerical results are obtained in support of a wind-tunnel test that was conducted in the National Transonic Facility at the NASA Langley Research Center. The model incorporated a generic fuselage and was mounted on the tunnel sidewall using a constant-width non-metric standoff. The computations were performed at to a nominal approach and landing flow conditions.The computed high-lift flow characteristics for the model in both the tunnel and in free-air environment are presented. The computed wing pressure distributions agreed well with the measured data and they both indicated a small effect due to the tunnel wall interference effects. However, the wall interference effects were found to be relatively more pronounced in the measured and the computed lift, drag and pitching moment. Although the magnitudes of the computed forces and moment were slightly off compared to the measured data, the increments due the wall interference effects were predicted reasonably well. The numerical results are also presented on the combined effects of the tunnel sidewall boundary layer and the standoff geometry on the fuselage forebody pressure distributions and the resulting impact on the configuration longitudinal aerodynamic characteristics.
Document ID
20020078006
Acquisition Source
Langley Research Center
Document Type
Technical Publication (TP)
Authors
Ghaffari, Farhad (NASA Langley Research Center Hampton, VA United States)
Biedron, Robert T. (NASA Langley Research Center Hampton, VA United States)
Luckring, James M. (NASA Langley Research Center Hampton, VA United States)
Date Acquired
September 7, 2013
Publication Date
August 1, 2002
Subject Category
Aerodynamics
Report/Patent Number
NASA/TP-2002-211779
NAS 1.60:211779
L-18111
Funding Number(s)
PROJECT: RTOP 522-31-31-06
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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