SMAAART TASK ORDER: STATEMENT OF WORK (SOW) TASK TITLE: 8-FOOT HIGH TEMPERATURE TUNNEL (8 HTT) LARGE-SCALE SCRAMJET ENGINE TEST TECHNIQUES (LSETT) TEST ENGINEERING SUPPORT 1.0 INTRODUCTION/BACKGROUND: NASAS HYPERSONIC PROJECT, THE AIR FORCE RESEARCH LABORATORY (AFRL), AND THE DEPARTMENT OF DEFENSES (DODS) TEST RESOURCE MANAGEMENT CENTERS ADVANCED PROPULSION TEST TECHNOLOGY FOCUS AREA HAVE ENTERED INTO A COLLABORATIVE TEST EFFORT TO QUANTIFY LARGE SCALE SCRAMJET TO FACILITY INTERACTIONS THAT AFFECT THE TEST ARTICLE PERFORMANCE. FUTURE PROGRAMS FROM ALL THREE AGENCIES FOCUS ON THE DEVELOPMENT OF INCREASINGLY LARGE SCRAMJET ENGINES. THERE ARE TWO EXISTING NATIONAL HYPERSONIC TEST FACILITIES USED TO PERFORM FREEJET TESTING OF SCRAMJET ENGINES. THE FIRST IS THE ARNOLD ENGINEERING DEVELOPMENT CENTERS AERODYNAMIC AND PROPULSION TEST UNIT (APTU) WHICH HAS A 42 DIAMETER HYPERSONIC TEST STREAM. THE SECOND IS THE NASA LANGLEY RESEARCH CENTER 8-FOOT HIGH TEMPERATURE TUNNEL WHICH HAS A 96 DIAMETER TEST STREAM. THE DEVELOPMENT OF LARGER SCRAMJET ENGINES PLACES NEW DEMANDS ON THESE TWO TEST FACILITIES AND RESULTS IN SIGNIFICANT INTERACTION BETWEEN THE TEST ENGINE AND THE TEST FACILITY. IT IS CRITICAL THAT THESE INTERACTIONS AND THE IMPACT THEY HAVE ON THE MEASURED ENGINE PERFORMANCE ARE PREDICTABLE AND WELL UNDERSTOOD. THE INCREASING SIZE OF FUTURE SCRAMJET ENGINES WILL RESULT IN BLOCKING A LARGE PORTION OF THE TEST FACILITY HYPERSONIC FLOW AND WILL ALSO REQUIRE TRUNCATION OF THE ENGINE INLET AND EXIT NOZZLE TO PHYSICALLY FIT INTO THE EXISTING TEST FACILITIES. THE TRUNCATION OF THE INLET AND NOZZLE, AS WELL AS THE LARGE FRACTION OF FLOW BLOCKAGE FOR THESE FUTURE LARGE ENGINES, WILL RESULT IN FACILITY INDUCED IMPACTS ON THE MEASURED ENGINE PERFORMANCE. THE FUTURE DEVELOPMENT AND PRODUCTION OF LARGE SCALE SCRAMJETS DEPEND HEAVILY ON THE ABILITY TO ACCURATELY PREDICT THE IMPACT OF THE TEST FACILITY ON THE MEASURED DATA. THE COLLABORATIVE TESTING EFFORT BETWEEN THE THREE ORGANIZATIONS WILL PRODUCE EXPERIMENTAL DATA ASSESSING THESE IMPACTS AND PROVIDING A BENCHMARK DATA SET RELATIVE TO TEST FACILITY / SCRAMJET INTERACTIONS. 2.0 SCOPE / OBJECTIVE(S): THE SCOPE OF THIS TASK IS TO PROVIDE TEST ENGINEERING SUPPORT FOR THE LSETT TEST IN THE NASA LANGLEY 8 HTT. THE TESTING IS SCHEDULED TO OCCUR DURING THE SECOND HALF OF FY 2011, BUT TEST PREPARATION IS REQUIRED TO BEGIN IN JANUARY 2011 IN ORDER TO MEET THE TEST SCHEDULE. THE OBJECTIVE OF LSETT TESTING IN THE 8 HTT IS TO TEST A CONTRACTOR DESIGNED SCRAMJET ENGINE WITH A FULL INLET AND NOZZLE IN THE 8 HTT AT MACH 5 FLIGHT CONDITIONS. 3.0 DESCRIPTION OF THE WORK/TASKS TO BE PERFORMED: THE CONTRACTOR SHALL PERFORM THE FOLLOWING TASKS: 3.1 TEST PLANNING AND DOCUMENTATION. 3.1.1 THE CONTRACTOR SHALL PARTICIPATE IN WEEKLY TELECONS TO DEFINE THE INTEGRATED RUN SEQUENCE REQUIRED FOR SAFE EXECUTION OF THE LSETT TEST IN THE 8 HTT. THE DEFINITION OF THE INTEGRATED RUN SEQUENCE SHALL BE A COLLABORATIVE EFFORT AND WILL BE MUTUALLY AGREED UPON BY THE CONTRACTOR AND NASA. THE COMPLETED INTEGRATED RUN SEQUENCE SHALL SATISFY ALL NASA LANGLEY TEST SAFETY REQUIREMENTS AND THE CONTRACTOR ENGINE OPERATING LIMITS. FINAL APPROVAL WILL BE GIVEN BY THE NASA TASK MONITOR (TM) VIA EMAIL TO THE CONTRACTORS PROJECT MANAGER (PM). THE CONTRACTOR SHALL UPDATE AND MAINTAIN THE DETAILED INTEGRATED RUN SEQUENCE DOCUMENT (IRSD) FOR WEEKLY REVIEW DURING THE TELECONS. (DELIVERABLE ITEM 4.3). THE INITIAL IRSD DRAFT WILL BE PROVIDED TO THE CONTRACTOR AS SPECIFIED UNDER GOVERNMENT FURNISHED INFORMATION (GFI) SOW 5.1. 3.1.2 THE CONTRACTOR SHALL DEVELOP, AT A MINIMUM, THE FOLLOWING FACILITY SYSTEMS VERIFICATION CHECK LISTS (DELIVERABLE ITEM 4.4): - ENGINE FUEL DELIVERY SYSTEM. - WATER COOLING SYSTEM PERFORMANCE. - SILANE IGNITOR GAS SYSTEM PERFORMANCE. - ANGLE OF ATTACH/MODEL ELEVATOR COORDINATION. - NORMAL STOP SEQUENCE OF EVENTS. - ABNORMAL STOP SEQUENCE