CFD analysis of flight-test configuration for LFC on swept wings
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Recent work using spanwise-periodic discrete roughness elements (DREs) has shown great promise as a means of controlling the crossflow instability responsible for transition over a swept wing without the need for a complex suction system. The Texas A&M Flight Research Lab (FRL) is currently conducting flight tests of a laminar flow 30° swept wing model (SWIFT) mounted vertically below the port wing hard-point of a Cessna O-2A Skymaster and operated at chord Reynolds numbers between 7 million and 7.5 million. As a companion to the flight experiments, the current study is concerned with modeling the basic-state flow around the 0-2 with the SWIFT model mounted on the port wing store pylon using a commercial Computational Fluid Dynamics (CFD) package. This basic-state solution serves two purposes. It is used to validate the flight test configuration and operating conditions, as well as establish accurate chordwise placement of the DRE's with the goal of achieving a minimum of 60% laminar flow over the suction (test) side of the model. Copyright © 2008 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
author list (cited authors)
Rhodes, R. G., Carpenter, A. L., Reed, H. L., & Saric, W. S.