CFD HAS A LONG HISTORY OF DEVELOPMENT AND USE FOR ENABLING BETTER DESIGNS AND FOR REDUCING COST RISK AND DESIGN CYCLE TIME FOR FIXED WING AIRCRAFT. HOWEVER OFTENTIMES CFD CAN ONLY BE USED WITH CONFIDENCE AT NEAR DESIGN CONDITIONS WHERE THE FLOW IS MOSTLY ATTACHED. THE ABILITY TO RELIABLY PREDICT FLOW SEPARATION INCLUDING SEPARATION ONSET AND PROGRESSION HAS BEEN IDENTIFIED AS ONE OF THE MAJORIMPEDIMENTS TO MORE EFFECTIVE USE OF COMPUTATIONAL METHODS THROUGHOUT THE DESIGN CYCLE. SUCCESSFUL DEMONSTRATION OF THIS CAPABILITY WILL ENABLE A BETTER UNDERSTANDING OF COMPLEX FLOW PHYSICS DRIVING IMPORTANT DESIGN METRICS WHICH IN TURN WILL ENABLE MORE AGGRESSIVE DESIGNS AT LOWER RISK. NEW CONCEPTS AND CONFIGURATIONS OFTEN RELY ON DIFFERENT FLOW PHYSICS THAT PROGRAMS MUST BE ABLE TO SIMULATE WITH CONFIDENCE IN ORDER TO OPTIMIZE DESIGNS AND REDUCE RISK. AT THE SAME TIME SIMULATIONS FOR TRADITIONAL FIXED WING CONFIGURATIONS ARE SEVERELY LACKING IN CRITICAL REGIONS OF THE FLIGHT REGIME SUCH AS NEAR STALL AT HIGH-LIFT CONDITIONS IN DEFLECTED CONTROL SURFACE CONDITIONS AND AT THE EDGES OF THE FLIGHT ENVELOPE. IN ALL THESE CASES THE ABILITY TO EXPAND THE USE OF CFD TO A WIDER VARIETY OF CONFIGURATIONS AND THROUGH ALL REGIONS OF THE FLIGHT ENVELOPE WILL GREATLY IMPACT ALL THE IMPORTANT PERFORMANCE METRICS SUCH AS DRAG FUEL BURN AND EMISSIONS ACOUSTICS FLOW CONTROL HIGH LIFT EFFECTIVENESS AND STABILITY AND CONTROL.THE OBJECTIVE OF THIS PROPOSAL IS TO DEVELOP AND DEMONSTRATE A CAPABILITY FOR ACCURATELY PREDICTING AERODYNAMIC FLOWS OVER REALISTIC AND COMPLEX CONFIGURATIONS INVOLVING SUBSTANTIAL AMOUNTS OF FLOW SEPARATION. ALTHOUGH REYNOLDS-AVERAGED NAVIER-STOKES (RANS) TURBULENCE MODELS CAN BE USED WITH HIGH CONFIDENCE FOR FULLY ATTACHED FLOWS OR FOR FLOWS WITH SMALL REGIONS OF SEPARATION RELIABLE ANDACCURATE SIMULATION OF AERODYNAMIC FLOWS WITH MODERATE TO MASSIVE REGIONS OF SEPARATION REMAINS CHALLENGING. BY RESOLVING A LARGER PORTION OF THE TURBULENCE SPECTRA TECHNIQUES SUCH AS LARGE-EDDY SIMULATION (LES) OFFER THE POTENTIAL FOR MORE UNIVERSALLY ACCURATE MODELS APPLICABLE TO A WIDER RANGE OF SEPARATED FLOWS. HOWEVER EXISTING LES METHODS FACE THREE BASIC PROBLEMS: A HUGE VARIETY OFLES MODELS ARE CURRENTLY APPLIED DYNAMIC LES METHODS ARE EITHER VERY EXPENSIVE OR HAVE TO BE COMBINED WITH FLOW-DEPENDENT EMPIRICAL STABILIZATION TECHNIQUES AND THE COST OF LES FOR WALL-BOUNDED FLOW SIMULATIONS ARE WAY TOO HIGH FOR MOST APPLICATIONS. A SOLUTION APPROACH FOR THESE THREE PROBLEMS WAS RECENTLY SUGGESTED BY THE PI. BY USING A STOCHASTIC TURBULENCE MODEL HE DEVELOPED A HIERARCHY OF REALIZABLE LES MODELS CORRESPONDING DYNAMIC LES METHODS THAT OVER-COME THE STABILITY PROBLEMS OF EXISTING DYNAMICLES METHODS AND UNIFIED RANS-LES MODELS THAT ENABLE A HUGE COMPUTATIONAL COST REDUCTION BY A FACTOR OF 5.7 RE^0.42 (RE REFERS TO THE REYNOLDS NUMBER). THESE NEW UNIFIED AND DYNAMIC LES METHODS HAVE SIGNIFICANT ADVANTAGES COMPARED TO EXISTING METHODS. ON THE OTHER HAND THERE ARE INDICATIONS THAT THESE METHODS DO NOT REPRESENT THE FINAL ANSWER TO THE THREE LES PROBLEMS DESCRIBED ABOVE BECAUSE OF THEIR DEFICIENCIES IN ACCURATELY REPRESENTING THE SPATIOTEMPORAL STRUCTURE OF TURBULENT FLOWS. THE FIRST SPECIFIC PROJECT GOAL IS TO OVERCOME THIS PROBLEM BY THE DEVELOPMENT OF A REALIZABLE STOCHASTIC TURBULENCE MODEL THAT PRESERVES THE SPACE-TIME STRUCTURE OF TURBULENCE AND TO USE THIS MODEL FOR THE DERIVATION OF HIERARCHICAL LES DYNAMIC LES AND UNIFIED RANS-LES METHODS. THE SECOND SPECIFIC PROJECT GOAL IS TO SHOW THE SUCCESS OF DYNAMIC LES AND UNIFIED RANS-LES METHODS THROUGH APPLICATIONS INVOLVING FLOW SEPARATION. THIS GOAL WILL BE ACCOMPLISHED BY A CAREFULLY ORGANIZED VALIDATION PLAN INVOLVING CANONICAL TEST CASES THE VALIDATION OF AIRFOIL SEPARATION AND STALL BEHAVIOR AND FINALLY THE STUDY OF COMPLEX VALIDATION CASES (MULTI-ELEMENT AIRFOILS/WINGS TIP VORTEX PREDICTION AND SHOCK BOUNDARY LAYER INTERACTION).