IGF::OT::IGF STATEMENT OF WORK (SOW) SMAAART TASK TITLE: SUPERSONIC COMBUSTION TESTS IN THE HYPULSE SHOCK TUBE FACILITY AND HIGH PRESSURE AIR UPGRADE FOR EXTENDED RUN TIME 1.0 INTRODUCTION/BACKGROUND: IN COORDINATION WITH THE NATIONAL CENTER FOR HYPERSONIC COMBINED CYCLE PROPULSION (NCHCCP), NASA INTENDS TO SUPPORT TESTING OF THE HY-V (HIGH-FIVE) SCRAMJET FLOWPATH MODEL IN THE HYPULSE SHOCK TUBE FACILITY LOCATED AT THE ATK GENERAL APPLIED SCIENCES LABORATORY (GASL) FACILITY IN RONKONKOMA, NY. HY-V WAS A PREVIOUSLY FUNDED PROGRAM BY THE DEPARTMENT OF DEFENSE (DOD) TEST RESOURCE MANAGEMENT CENTERS ADVANCED PROPULSION TEST TECHNOLOGY (SINCE RENAMED HIGH SPEED SYSTEMS TEST) FOCUS AREA. THIS TESTING WILL PRODUCE A DATABASE FOR SUPERSONIC COMBUSTION AT SIMULATED HYPERVELOCITY FLIGHT SPEEDS WHICH WILL BE UTILIZED TO HELP IMPROVE THE UNDERSTANDING OF THE COMPLEX PHYSICS WITHIN A SCRAMJET COMBUSTOR. THIS IS RELEVANT TO ON-GOING WORK FOR THE HYPERSONICS PROJECT WHERE THE GOAL IS ULTIMATELY TO BE ABLE TO DESIGN HIGHER PERFORMANCE SCRAMJET COMBUSTORS. THE SCRAMJET MIXING AND COMBUSTION PROCESSES ARE KNOWN TO HAVE THE GREATEST POTENTIAL FOR IMPROVING SCRAMJET ENGINE PERFORMANCE AND EFFICIENCY. THE TESTING WILL EXTEND THE HYPERVELOCITY SCRAMJET CAPABILITY OF BOTH THE NASA HYPERSONICS PROJECT AND THE NCHCCP, ALSO KNOWN AS THE CENTER. THIS TASK WILL LEVERAGE THE EXISTING HARDWARE AND DATA OF THE HY-V TEST PROGRAM. THE HYPULSE FACILITY WILL BE OPERATED IN REFLECTED SHOCK TUBE (RST) MODE TO SIMULATE A FLIGHT MACH NUMBER OF 7 AND 10 WITH CLEAN AIR TEST GAS. THIS FACILITY IS OPERATED BY ATK GASL. FUEL PLUME IMAGING (FPI), AND TUNABLE DIODE LASER ABSORPTION SPECTROSCOPY (TDLAS) ALONG WITH TRADITIONAL WALL PRESSURE AND HEAT FLUX MEASUREMENTS WILL BE CONDUCTED. THE IMAGING WILL BE USED PRIMARILY FOR QUALITATIVE OBSERVATION TO GIVE INSIGHT INTO FLOW PHYSICS AND IN COMPARISON AGAINST COMPUTATIONAL MODELING AS WELL AS THE TRADITIONAL WALL PRESSURE AND HEAT FLUX MEASUREMENTS FOR THE SAME PURPOSES. THESE DATA WILL BE POST-PROCESSED INTO A DATABASE TO BE COMPARED AGAINST COMPUTATIONAL FLUID DYNAMICS (CFD) MODELS. ALSO IN COORDINATION WITH THE TEST RESOURCE MANAGEMENT CENTERS (TRMCS) HIGH SPEED SYSTEM TEST (HSST) TECHNOLOGY AREA, NASA INTENDS TO SUPPORT THE LARGE-SCALE SCRAMJET ENGINE TEST TECHNOLOGY (LSETT) TESTS AT GASL AND DEVELOPMENT OF THE HYPERSONIC AIRBREATHING PROPULSION CLEAN AIR TESTBED (HAPCAT), A NEW TEST CAPABILITY BEING BUILT AT ATK GASL. THE LSETT TESTS AT GASL WILL EXPLORE THE ACCURACY OF SEMI-FREEJET AND DIRECT CONNECT TEST METHODS, CONDUCTED UNDER AIR FORCE RESEARCH LABORATORY (AFRL) CONTRACT F33615-03-D-2416 DO 021 WITH ATK. AN UPGRADE TO THE GASL HIGH PRESSURE AIR SYSTEM IS NECESSARY TO PROVIDE SUFFICIENT RUN TIME FOR THESE TESTS. ADDITIONAL HIGH PRESSURE AIR CAPACITY IS ALSO REQUIRED TO FULLY UTILIZE THE CAPABILITIES OF THE HAPCAT FACILITY, WHICH WILL BE USED TO TEST HYPERSONIC PROPULSION TECHNOLOGY UNDER VARIABLE CONDITIONS FROM MACH 5 TO 8. BOTH OF THESE EFFORTS ARE RELEVANT TO ON-GOING WORK OF THE HYPERSONICS PROJECT WHERE THE GOAL IS ULTIMATELY TO BE ABLE TO DESIGN LARGER AND HIGHER PERFORMANCE SCRAMJET COMBUSTORS. 2.0 SCOPE AND OBJECTIVES: THE SCOPE OF THIS TASK ORDER ENTAILS TWO EFFORTS. FIRST IS TO APPLY OPTICAL IMAGING IN CONJUNCTION WITH CONVENTIONAL MEASUREMENTS TO EXAMINE SUPERSONIC MIXING AND COMBUSTION IN THE HY-V FLOWPATH MODEL. SECOND IS TO INCREASE THE HIGH PRESSURE AIR STORAGE CAPACITY AT GASL IN ORDER TO BE ABLE TO ACHIEVE REQUIRED TEST DURATIONS FOR THE LSETT AND HAPCAT PROJECTS. EXTENDED RUN TIME SUPPORTS NASAS NEED TO CHARACTERIZE THE PERFORMANCE OF FUEL COOLED SCRAMJET ENGINES. THE OBJECTIVES OF THIS TASK ORDER ARE TO: 1) CONDUCT FPI, SCHLIEREN IMAGING, TDLAS WATER CONCENTRATION AND TEMPERATURE MEASUREMENTS, AND PRESSURE AND HEAT FLUX MEASUREMENTS ON THE HY-V FLOWPATH A AT MACH 7 SIMULATED FLIGHT SPEED. 2) CONDUCT FPI, SCHLIEREN IMAGING, TDLAS WATER CONCENTRATION AND TEMPERATU