MEASUREMENT OF VORTEX FLOWFIELDS

MANY SUPERSONIC AIRCRAFT GENERATE VORTICES AT HIGHLY-SWEPT LEADING EDGES WHICH GENERALLY AUGMENT THE LIFT. HOWEVER, OUR CURRENT UNDERSTANDING OF VORTEX, VISCOUS/INVISCID INTERACTIONS IS INSUFFICIENT TO ALLOW COMPUTATIONAL DESIGN WITHOUT RECOURSE TO EXPERIMENTAL DOCUMENTATION AND CONFIRMATION. THE PURPOSE OF THIS PROPOSAL, SUBMITTED IN RESPONSE TO SUBTOPIC 02.09 - CONFIGURATIONAL AERODYNAMICS INCLUDING VORTICES, IS TO DEVELOP EXPERIMENTAL METHODS AND OBTAIN DATA WHICH WILL IMPROVE OUR KNOWLEDGE OF VORTEX DOMINATED FLOWS. THE RESULTS WILL BE USED TO DEVELOP EMPIRICAL TURBULENCE MODELS AND TO VALIDATE THE MOST PROMISING EULER AND NAVIER-STOKES CODES WHICH ARE PLANNED FOR USE ON FUTURE COMPUTATIONAL DESIGNS OF ADVANCED TECHNOLOGY, THREE DIMENSIONAL WINGS.