THE ULTIMATE OBJECTIVE OF THIS PROPOSED WORK IS THE DEVELOPMENT OF THE CAPABILITY TO DESIGN AND PREDICT OF THE PERFORMANCE OF HIGH EXPANSION-RATIO OPTIMIZED-CONTOUR NOZZLES.

THE ULTIMATE OBJECTIVE OF THIS PROPOSED WORK IS THE DEVELOPMENT OF THE CAPABILITY TO DESIGN AND PREDICT OF THE PERFORMANCE OF HIGH EXPANSION-RATIO OPTIMIZED-CONTOUR NOZZLES. CURRENT PROCEDURES AND COMPUTATIONAL TOOLS ARE APPLICABLE ONLY TO LARGE ENGINES AND MODERATE EXPANSION RATIOS. A NEED EXISTS TO DESIGN VERY HIGH EXPANSION RATIO NOZZLES WITH OPTIMIZED CONTOURS WHICH WILL FULLY EXPLOIT THE VACUUM SPECIFIC IMPLUSE SYSTEM AND PROPELLANT COMBINATION POTENTIALS. BEFORE ANY RESOURCES ARE COMMITTED TO ANY NOZZLE OPTIMIZATION, IT IS NECESSARY TO UPDATE AND IMPROVE PRESENT METHODS. ERGO-TECH PROPOSES THE DEVELOPMENT OF NEW PROCEDURES AND THE MODIFICATION OF EXISTING SOFTWARE TO OPTIMIZE THE DESIGN OF SPACE ENGINES NOXXLES AND VERIFY THEIR PERFORMANCE, TAKING ADVANTAGE OF THE EXPERIMENTAL PROGRAM WHICH IS PRESENTLY UNDER WAY AT AFRPL. IN PHASE I, THE PREDICTION CAPABILITIES AND RANGE OF APPLICABILITY OF THE EXISTING CODES (SPP,TDK, BLIMP, BLM ANDRAO'S PROGRAM) WILL BE SUBJECTED TO A SENSITIVITY ANALYSIS , AND A SET OF PARAMETERS AND ENGINE OPERATING CONDITIONS WILL BE SELECTED FOR TEST VERIFICATION. IN PASE II, ADDITIONAL SOFTWARE WILL BE DEVELOPED, AND CORRECT PROCEDURES ESTABLISHED. IN PHASE III THE DEVELOPMENT CAPABILITIES WILL BE MARKETED THROUGHOUT AEROSPACE INDUSTRY.