COMPUTATIONAL MODEL FOR THRUST REVERSING/VECTORING JET

COMPUTATIONAL FLUID DYNAMICS (CFD) OFFERS SIGNIFICANT OPPORTUNITIES IN THE DESIGN OF V/STOL FIGHTER AIRCRAFT. THERE IS ENORMOUS SCOPE FOR A SYNERGISM BETWEEN CFD AND WIND TUNNEL TESTING, AFFORDING GREATER EFFICIENCY IN THE REDUCTION OF DATA AND A QUICKER GRASP OF ITS SIGNIFICANCE. MOREOVER, CFD SHOULD BE ABLE TO DRASTICALLY REDUCE THE NUMBER OF TESTS THAT ARE NEEDED. THE OVERALL PROJECT OBJECTIVE IS TO DEVELOP A TIME-DEPENDENT, COMPRESSIBLE, THREE-DIMENSIONAL, NAVIER-STOKES MODEL(S) FOR THRUST VECTORING/REVERSING JETS. THE PROPOSED APPROACH IS TO USE THE CFD CODE FLUENT TO SIMULATE SELECTED SUBSONIC FLOW FIELD FOR WHICH EXPERIMENTAL DATA EXISTING USING THE STANDARD K-E MODEL AND THE HIGHER ORDER ALGEBRAIC STRESS MODEL (ASM). BASED ON THE COMPARISON OF THE SIMULATIONS WITH DATA, THE MOST EFFICIENT APPROACH IN TERMS OF PREDICTION ACCURACY AND COMPUTATIONAL SPEED WILL BE DETERMINED. THE MODELS AND COMPUTATIONAL APPROACHES SELECTED IN PHASE I WILL BE IMPLEMENTED IN PHASE II TO PRODUCE THE DESIRED CODE FOR THRUST VECTORING/REVERSING JETS. THE PHASE II IMPLEMENTATION WILL INCLUDE REFINEMENT AND ENHANCEMENT OF THE GRID AND SELECTED TURBULENCE MODELS, AND IF DESIRED, INCORPORATION OF LARGE EDDY SIMULATION (LES) MODELS AND OTHER CFD CODES DEVELOPED AT CREARE WHICH USE ADVANCED MULTI-GRID SOLUTION TECHNIQUES.