Statistics – Computation
Scientific paper
Jan 1995
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1995stin...9717022l&link_type=abstract
Conference Paper, Applied Aerodynamics
Statistics
Computation
High Reynolds Number, Airfoils, Wind Tunnel Tests, Structured Grids (Mathematics), Navier-Stokes Equation, Computational Fluid Dynamics, Flapping, Camber, Pressure Distribution, Leading Edges, Trailing Edges, Lift, Prediction Analysis Techniques, Data Correlation
Scientific paper
New high-lift components have been designed for a three-element advanced high-lift research airfoil using a state-of-the-art computational method. The new components were designed with the aim to provide high maximum-lift values while maintaining attached flow on the single-segment flap at approach conditions. This three-element airfoil has been tested in the NASA Langley Low-Turbulence Pressure Tunnel at chord Reynolds number up to 16 million. The performance of the NASA research airfoil is compared to a reference advanced high-lift research airfoil. Effects of Reynolds number on slat and flap rigging have been studied experimentally. The performance trend of this new high-lift design is comparable to that predicted by the computational method over much of the angle of attack range. Nevertheless, the method did not accurately predict the airfoil performance or the configuration-based trends near maximum lift.
Dominik Chet J.
Lin John C.
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