Navier-Stokes solutions about the F/A-18 wing-LEX-fuselage configuration with multi-block structured gridsThree-dimensional thin-layer Navier-Stokes computations are presented for the F/A-18 configuration. The modeled configuration includes an accurate surface representation of the fuselage, leading-edge-extension, as well as the wing with and without leading-edge-flap deflection. A multi-block structured volume grid with various topologies is generated using transfinite interpolation technique. The flowfield domain is divided into twenty blocks, each representing a particular geometrical complexity of the configuration. The results are obtained from an algorithm for solving the compressible Navier-Stokes equations that incorporates an upwind-biased, flux-difference-splitting approach. In addition, a newly developed capability that allows for generalized surface patching among blocks is employed. Turbulent results are presented for flow conditions that correspond to recent NASA F/A-18 High Alpha Research Vehicle flight experiments. Good correlations between the computations and the flight test results are disclosed for both surface flow patterns as well as surface pressure distributions.
Document ID
19910069166
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Ghaffari, Farhad (NASA Langley Research Center Hampton, VA, United States)
Luckring, James M. (NASA Langley Research Center Hampton, VA, United States)
Thomas, James L. (NASA Langley Research Center Hampton, VA, United States)
Bates, Brent L. (Vigyan, Inc. Hampton, VA, United States)
Biedron, Robert T. (Analytical Services and Materials, Inc. Hampton, VA, United States)