Task order - statement of work (SOW) task title: ERA integrated advanced wing technology demonstration flight test options study 1.0 introduction/background: the goal of the integrated systems…

Task order - statement of work (SOW) task title: ERA integrated advanced wing technology demonstration flight test options study 1.0 introduction/background: the goal of the integrated systems research program (isrp) within nasas aeronautics research mission directorate (armd) is to conduct research at an integrated system level on promising concepts and technologies for commercial transport-class vehicles and demonstrate the benefits in a relevant environment. The environmentally responsible aviation (ERA) project, a project of isrp, has the goal to explore and assess new vehicle concepts and enable technologies through system-level experimentation to reduce fuel burn, noise and emissions. System studies have shown that laminar flow control (i.e., delay of boundary layer transition) is one of the key technologies required to meet the ERA system level metrics because of the significant realizable reduction of skin friction drag. Therefore, the drag reduction element of the ERA project primarily focuses on maturation of key technologies to demonstrate the practical feasibility of laminar flow control. In order to investigate swept-wing laminar flow technology, NASA intends to utilize a two-phase process. Phase i encompasses the effort of this task order. Phase II (if NASA decides to proceed), will be for the execution of the program defined during phase i. 2.0 scope and objective(s): 2.1 the scope of this task order (phase i) is to investigate options for executing a test program that would enable the advanced aerodynamic and structural concepts relevant to commercial transport-class vehicles (hereinafter referred to as ERA vehicles) by maturing key aerodynamic and structural technologies to technology readiness level (TRL) and manufacturing readiness level (MRL) 6. Of specific interest are options for demonstrating swept-wing laminar flow (swlf) to maximize achievable natural laminar flow reynolds numbers at commercial transport relevant conditions. 2.2 the objective of this task order (phase i) is to define an integrated advanced wing technology demonstration (iawtd) program (to be executed in phase II) that includes wing design concepts with loading and sweep angles appropriate for efficient 0.85 mach number flight for ranges and payloads typical of commercial transport vehicles, including demonstration of swept-wing laminar flow with and without discrete roughness elements (DRE). 3.0 description of the work/tasks to be performed: the contractor shall perform the following tasks: 3.1 vehicle and wing concept identification 3.1.1 the contractor shall conduct a study to examine the potential ERA vehicles to determine the best options for candidate wing sections to provide requirements for conducting the phase II flight tests to achieve SOW 2.2 objective. 3.1.2 the contractor shall estimate, based on ERA vehicles in task 3.1.1, various wing properties including average wing loading, bending moments, and transition reynolds numbers. These properties are to be compared to existing structural and swlf capabilities to clearly indicate the promised advancements with respect to the current state of the art. 3.1.3 the contractor shall define iawtd program elements, including ground and flight tests, required to achieve the overall objective of SOW 2.2. 3.1.4 the contractor shall define a draft set of top level requirements for the iawtd program. In defining the top level requirements, the contractor is to assess importance and significance of scaling for both the swept-wing laminar flow and structural test aspects. 3.2 test approach, swept wing laminar flow and integrated structural demonstration 3.2.1 the contractor shall define all necessary steps and schedule required to execute the iawtd program during phase II. These steps shall include, but not limited to: 3.2.1.1 the facilities required to execute ground test and flight test elements. 3.2.1.2 NASA assets THA