IGF::OT::IGF OTHER FUNCTIONS - STATEMENT OF WORK (SOW) SMAAART TASK TITLE: AHSTF ENHANCED MIXING RESEARCH PROJECT 1.0 INTRODUCTION/BACKGROUND: THE HYPERSONIC AIRBREATHING PROPULSION BRANCH (HAPB) AT NASA LANGLEY RESEARCH CENTER (LARC) RECENTLY INITIATED THE AHSTF ENHANCED MIXING RESEARCH PROJECT WHICH SEEKS TO MEET FUTURE HYPERSONIC RESEARCH REQUIREMENTS. THE PURPOSE OF THIS PROJECT IS TO INVESTIGATE AND DEVELOP FLIGHT SIMULATION CAPABILITY AND IMPROVE THE ABILITY TO ASSESS FLOW QUALITY FOR HYPERSONIC RESEARCH. IMPROVED DIAGNOSTICS AND MEASUREMENT SYSTEMS ARE NEEDED TO ROUTINELY QUANTIFY THE FLOW PROPERTIES DELIVERED TO THE TEST ARTICLES. THIS PROJECT ALSO INCLUDES INVESTIGATING FUEL INJECTION AND MIXING FOR SCRAMJET ENGINES TO ENHANCE OUR UNDERSTANDING OF SCRAMJET FUEL INJECTION AND MIXING DEVICES IN A CONTROLLED TEST ENVIRONMENT TO EVALUATE INNOVATIVE CONCEPTS. SINCE THE SCRAMJET MIXING AND COMBUSTION PROCESSES ARE KNOWN TO HAVE THE GREATEST POTENTIAL FOR IMPROVING SCRAMJET ENGINE PERFORMANCE AND EFFICIENCY, THIS PROJECT SEEKS TO PROVIDE A MAJOR STEP TOWARDS DEVELOPING PRACTICAL PROPULSION SYSTEMS FOR AEROSPACE VEHICLES OPERATING IN THE HYPERSONIC SPEED REGIME. THE AHSTF ENHANCED MIXING RESEARCH PROJECT, SCHEDULED TO BE IMPLEMENTED IN FISCAL YEAR (FY) 13, INVOLVES THE RESEARCH, DEVELOPMENT, AND INSTALLATION OF TWO NEW FACILITY NOZZLES (I.E., MACH 3.5 AND MACH 2.2) TO DEMONSTRATE MACH 2.5 TO 4.0 FLIGHT SIMULATED CONDITIONS. 2.0 SCOPE AND OBJECTIVE(S): THE SCOPE OF THIS TASK ORDER IS TO RESEARCH, PROCURE, AND DEVELOP THE AHSTF WITH MAJOR HARDWARE COMPONENTS NECESSARY TO SUCCESSFULLY COMPLETE THE AHSTF ENHANCED MIXING PROJECT. THE OBJECTIVES OF THIS TASK ORDER ARE TO OBTAIN: 1) PROCURE FACILITY TEST HARDWARE. 2) TEST AND EVALUATE VARIOUS FUEL INJECTION AND MIXING DEVICES IN THE AHSTF. 3.0 DESCRIPTION OF THE WORK/TASKS TO BE PERFORMED: THE CONTACTOR SHALL DESIGN, ANALYZE, AND FABRICATE THE FOLLOWING COMPONENT(S): 1) A MACH 3.5 FACILITY NOZZLE. 2) A MACH 2.2 FACILITY NOZZLE. 3) A RAKE TRAVERSE SYSTEM. 4) THREE (3) IN-STREAM RAKES FOR THE FACILITY NOZZLE EXIT. 5) THREE (3) IN-STREAM RAKES FOR THE MIXING TEST APPARATUS. 6) A GAS COMPOSITION MEASUREMENT SYSTEM. 7) FOUR (4) FACILITY NOZZLE JET STRETCHERS. NOTE: LARC WILL BE RESPONSIBLE FOR THE INSTALLATION AND INTEGRATION OF THIS HARDWARE INTO THE AHSFT. A CAD IMAGE OF THE AHSTF, WITH ITS MIXING TEST APPARATUS INSTALLED IN THE TEST CABIN IS SHOWN IN SOW 8.1. THE RAKE TRAVERSE SYSTEM AND IN-STREAM RAKES WILL BE USED TO SURVEY THE FLOW OVER A RANGE OF AXIAL LOCATIONS ALONG THE TEST CABIN FROM THE NOZZLE EXIT TO THE END OF THE MIXING REGION. GENERAL REQUIREMENTS: A) ALL HARDWARE SHALL INTEGRATE/INSTALL WITHIN THE AHSTF. B) ALL HARDWARE SHALL INCORPORATE DESIGN FEATURES THAT REDUCE MAINTENANCE TIME. DESIGN CHOICES THAT ALLOW DAY SHIFT CONFIGURATION CHANGES ARE PREFERRED AS LONG AS THEY DO NOT COMPROMISE THE FUNCTIONALITY OR DESIGN LIFE. C) ALL FLUID, ELECTRICAL, AND INSTRUMENTATION LINES SHALL INCORPORATE MATCHING CONNECTION TO THE ADJOINING FACILITY INTERFACE. D) ALL HARDWARE SHALL COMPLY WITH LANGLEY PROCEDURAL REQUIREMENT (LPR) 1710.15 ENTITLED WIND TUNNEL MODEL SYSTEMS CRITERIA (GFI 5.1). THE CONTRACTOR SHALL PERFORM THE FOLLOWING TASKS: 3.1 MACH 3.5 AND MACH 2.2 FACILITY NOZZLES THE GOVERNMENT HAS DEVELOPED THE REQUIREMENTS FOR THE FACILITY NOZZLES WITH THE INTENT TO MINIMIZE HARDWARE DESIGN AND FABRICATION COSTS BY LIMITING THE MAXIMUM OPERATING TEMPERATURE TO LEVELS CONSISTENT WITH UN-COOLED HARDWARE. THE DESIGN SHALL TAKE ADVANTAGE OF MATERIALS AND THERMAL MANAGEMENT THAT PROVIDES THE BEST TRADE-OFF BETWEEN COST AND DIMENSIONAL TOLERANCE. 3.1.1 THE CONTRACTOR SHALL DESIGN, ANALYZE, AND DELIVER ENGINEERING DRAWINGS FOR A MACH 3.5 FACILITY NOZZLE AND A MACH 2.2 FACILITY NOZZLE WHICH DELIVER FLOW TO THE TEST CABIN/EXPERIMENT HARDWARE. A. EACH NOZZLE SHALL MATE WITH EX