THIS PROPOSAL ADDRESSES SUBTOPIC 2.1.2 "ACCURATE AND EFFICIENT MODELS FOR SCALE RESOLVING SIMULATIONS". THE OVERALL OBJECTIVE OF THIS PROPOSAL IS TO ADVANCE THE WALL-MODELED LARGE EDDY SIMULATION (WMLES) TECHNOLOGY TO THE POINT WHERE IT CAN BE ROUTINELY APPLIED TO REALISTIC PROBLEMS WITH CONFIDENCE IN THE RESULTING FLOW PREDICTIONS. THIS OBJECTIVE IS ENTIRELY IN LINE WITH NASA'S CFD VISION 2030 STUDY ENABLING BETTER FLOW PREDICTIONS AT THE EDGE OF THE OPERATIONAL ENVELOPE AT REALISTIC FLIGHT CONDITIONS. THE PROPOSAL IS FOCUSED ON DEVELOPING A SYSTEMATIC ALGORITHM-DRIVEN ADAPTIVE APPROACH TO FINDING THE RIGHT GRID AND THE RIGHT LOCATION OF THE MODELING INTERFACE IN THE WMLES METHOD. THESE FACTORS (THE GRID AND THE MODELING INTERFACE) ARE THE TWO MOST IMPORTANT FACTORS DETERMINING THE ACCURACY AND TRUSTWORTHINESS OF A WMLES PREDICTION. THE IMPORTANCE OF GRID-ADAPTATION STEMS FROM THE OBSERVATION THAT THE GRID IS THE SINGLE MOST IMPORTANT FACTOR DETERMINING THE QUALITY (ACCURACY RELIABILITY) OF A WMLES. THIS IS TRUE FOR LES IN A GENERAL SENSE AND ALSO MORE SPECIFICALLY FOR WMLES SINCE THE GRID RESOLUTION NEAR THE MODELING INTERFACE IS KNOWN TO CONTROL THE MAJORITY OF THE ERROR IN WMLES. DESPITE THE IMPORTANCE OF GRID ADAPTATION FOR LES THE PROBLEM HAS RECEIVED VERY LITTLE ATTENTION IN THE LITERATURE. THE SECOND FOCUS OF THIS PROPOSAL IS THE PROBLEM OF WHERE TO PLACE THE INTERFACE BETWEEN THE LES REGION AND THE WALL-MODELED REGION. THEORY CLEARLY SHOWS THAT THIS INTERFACE SHOULD BE PLACED AT 10-20% OF THE BOUNDARY LAYER THICKNESS FOR EQUILIBRIUM BOUNDARY LAYERS BUT THIS KNOWLEDGE IS NOT SUFFICIENT IN COMPLEX FLOWS WHERE THE BOUNDARY LAYER THICKNESS IS: (A) UNKNOWN A PRIORI; (B) CHANGES DRAMATICALLY IN SPACE; AND (C) MAY NOT EVEN BE A WELL DEFINED QUANTITY (E.G. IN THE CASE OF CONFLUENT BOUNDARY LAYERS). OUR OBJECTIVE IS TO DEVELOP A SYSTEMATIC AND ALGORITHM-DRIVEN (AS OPPOSED TO USER-DRIVEN) WAY TO PLACE THE MODELING INTERFACE AND TO FULLY INTEGRATE THIS ADAPTIVITY OF THE MODELING INTERFACE WITH THE ADAPTIVITY OF THE GRID. THE DEVELOPMENTS IN THIS WORK WILL BE ASSESSED ON A SEQUENCE OF FLOW PROBLEMS INCLUDING THE NASA WALL-MOUNTED HUMP A CHANNEL WITH SPANWISE FORCING AND A 3D AXISYMMETRIC HILL GEOMETRY. WE ARE PARTICULARLY INTERESTED IN FLOW PROBLEMS WITH 3D EFFECTS I.E. WHERE THE MEAN STREAMLINES ARE CURVED IN THE PLANE OF THE WALL (E.G. THE BACK OF A SWEPT WING).