STATEMENT OF WORK FOR DEVELOPMENT OF THE INTEGRATED MODELING AND VERIFICATION OF HYBRID WING-BODY, LOW NOIS…

Public award description

STATEMENT OF WORK FOR DEVELOPMENT OF THE INTEGRATED MODELING AND VERIFICATION OF HYBRID WING-BODY, LOW NOISE ESTOL AIRCRAFT RESEARCH OPPORTUNITIES IN AERONAUTICS - 2006 (ROA-2006), NRA-NNH06ZEA001N-SSFW2, PROPOSAL: 06-SSFW2-06-0058 1.0 INTRODUCTION/BACKGROUND THIS EFFORT IS DIVIDED INTO TWO PHASES. PHASE I IS A 1-YEAR BASE PERIOD, AND PHASE II IS A 2-YEAR OPTION PERIOD. THE PURPOSE OF THIS EFFORT IS TO DEVELOP AND VALIDATE PREDICTIVE CAPABILITIES FOR THE DESIGN AND PERFORMANCE OF CRUISE EFFICIENT, SHORT TAKE-OFF AND LANDING (CESTOL) SUBSONIC AIRCRAFT, AND TO VALIDATE PREDICTIVE CAPABILITIES FOR AN ESTIMATE OF CESTOL AIRCRAFT NOISE DURING TAKEOFF AND LANDING. FOR PHASE I (I.E., YEAR 1 BASE PERIOD), THESE METHODOLOGIES WILL BE THEN BE USED TO ACHIEVE THE FINAL OBJECTIVE OF YEAR 1, WHICH IS TO SELECT AND FURTHER REFINE ONE CESTOL CONCEPT AND THEN TO COMPLETE A PRELIMINARY DESIGN OF A LARGE SCALE WIND TUNNEL MODEL AND TEST. FOR PHASE II (I.E., YEARS 2 AND 3 OPTION PERIOD), THE WIND TUNNEL DESIGN AND CONSTRUCTION IS TO BE COMPLETED IN YEAR 2, AND A LARGE SCALE WIND TUNNEL TEST IS TO BE COMPLETED IN YEAR 3. THE FINAL OBJECTIVE OF PHASE II IS THE DEVELOPMENT VERIFICATION OF PREDICTIVE CODES FOR THESE ADVANCED POWERED-LIFT CONCEPTS AND THE GENERATION OF AN OPEN COLLECTION OF WIND TUNNEL DATA THAT CAN BE USED BY MODELERS TO IMPROVE THE CAPABILITY OF MODELING THESE COMPLEX FLOWS. IT IS INTENDED THAT THE PHASE I AND PHASE II (IF OPTION IS EXERCISED) EFFORT WILL ADDRESS THE FOLLOWING TOPICS:  LOW-SPEED AERODYNAMIC CHARACTERISTICS UP TO AND BEYOND MAXIMUM LIFT VIA A COMBINATION OF COMPUTATIONAL AND EXPERIMENTAL EFFORTS IN ORDER TO OBTAIN A MORE COMPLETE PICTURE OF THE FLOW PHYSICS.  ACOUSTIC CHARACTERISTICS OF A LOW-NOISE HYBRID WING-BODY SYSTEM VIA EXPERIMENTAL EFFORTS AND NOISE SIGNATURE MODELING TO ANALYZE NOT JUST THE NOISE GENERATED BY THE VEHICLE, BUT ALSO TO ANALYZE THE NOISE FOOTPRINT AROUND THE AIRPORT DURING TAKEOFF AND LANDING. 2.0 SCOPE OF WORK PHASE I WILL CONDUCT A PRELIMINARY DESIGN STUDY TO DETERMINE THE HYBRID WING-BODY DESIGN TO BE ANALYZED IN PHASE II, INCLUDING POWERED LIFT AERODYNAMIC STUDIES, BOTH COMPUTATIONAL AND EXPERIMENTAL, TO BETTER UNDERSTAND OF THE FLOW PHYSICS ASSOCIATED WITH USING THE PROPULSION SYSTEM TO IMPROVE THE AIRCRAFT LIFTING CAPABILITY. PHASE II WILL EXPAND THE UNDERSTANDING OF THE PHYSICS OF THE FLOW FIELD ASSOCIATED WITH POWERED LIFT CONFIGURATIONS. THE DESIGN DETERMINED FROM PHASE I WILL BE THE FOCUS OF BOTH THE EXPERIMENTAL AND COMPUTATIONAL EFFORTS. THE PROPULSION MODELING WILL BE FOCUSED ON METHODS OF IMPROVING THE AERODYNAMIC PREDICTIVE CAPABILITIES. THE LARGE SCALE WIND TUNNEL MODEL EFFORT IN YEAR 2 WILL FOCUS ON FINALIZING THE WIND TUNNEL MODEL, ASSEMBLING THE TEST PLAN, AND SCHEDULING THE EXPERIMENT IN THE CHOSEN FACILITY. YEAR 3 FOR THE LARGE SCALE WIND TUNNEL MODEL EFFORT WILL FOCUS ON PERFORMING THE EXPERIMENTS, ANALYZING THE RESULTS, AND PREPARING THE RESULTS FOR RELEASE. PHASE II WILL CONCLUDE WITH THE RELEASE OF THE ENTIRE DATA (INCLUDING WIND TUNNEL GEOMETRIES, RESULTING DATA, COMPUTATIONAL GEOMETRY MODELS AND CFD CONFIGURATION FILES) TO NASA AND THE GENERAL RESEARCH COMMUNITY, IF POSSIBLE. THE CONTRACTOR SHALL NOT CONSIDER ANY DATA GENERATED FROM THIS EFFORT AS PROPRIETARY AND WILL RELEASE ALL OF THE DATA THAT IT IS LEGALLY ALLOWED TO RELEASE TO THE GENERAL RESEARCH COMMUNITY. NASA WILL ENSURE THAT AS MUCH OF THESE RESULTS AS POSSIBLE ARE ABLE TO BE RELEASED TO THE GENERAL RESEARCH COMMUNITY WITHOUT LEGAL RESTRICTION.