Task order - statement of work (SOW) task title: hybrid wing body engine/airframe operability testing 1.0 introduction/background: the environmentally responsible aviation (ERA) project within the…

Task order - statement of work (SOW) task title: hybrid wing body engine/airframe operability testing 1.0 introduction/background: the environmentally responsible aviation (ERA) project within the integrated systems research program (isrp) of the NASA aeronautics research mission directorate (armd) has the responsibility to explore and document the feasibility, benefits, and technical risk of vehicle concepts and enabling technologies that will reduce the impact of aviation on the environment. The primary goal of the ERA project is to select vehicle concepts and technologies that can simultaneously reduce noise, fuel burn, and emissions. In addition, the ERA project will identify and mitigate technical risk and transfer knowledge to the aeronautics community at large so that new technologies and vehicle concepts can be incorporated into the future design of aircraft. The ERA project is a 6-year, two-phase project with several integrated technology demonstration (ITD) work packages that are currently defined for phase II (FY13-FY15). The ERA project (phase i) concluded an advanced vehicle concepts (AVC) study in january 2012 under NASA dryden contract NND11AG03C with boeing that identified advanced integrated vehicle concepts and component technology concepts that will allow subsonic transport aircraft to simultaneously meet the NASA system level goals of reduced noise, emissions, and fuel burn in the 2025 (or beyond) timeframe. Boeings final report under this contract defined a hybrid wing body (HWB) preferred system concept vehicle that simultaneously achieved all system level goals. In that system study, many assumptions were made as to the installation effects of ultra high bypass ratio (uhbr) ratio engines on the upper surface of the vehicle concept. There is significant uncertainty in many of those assumptions. In addition, many other important aspects of engine airframe integration were beyond the scope of the NASA dryden AVC study. Issues like installation drag increments on vehicle performance and forebody dominated flows (especially at low speeds and high angles of attack and sideslip) could have significant impact on the operability of uhbr engines mounted on the upper surface of HWB advanced vehicle concepts. These propulsion/airframe integration (PAI) driven issues must be examined to reduce the uncertainty in the avcs performance and will be the focus of PAI efforts conducted in ERA phase II. The planning process for ERA project phase II involved several key decision points where various technologies were evaluated and some were selected for further development under several ITD work packages. One of those ITD work packages given authority to proceed by armd included the assessment of uhbr engine operability on a HWB advanced vehicle concept. As part of this ITD work package, the space act agreement (SAA) SAA1-1018, annex 7 plans to capture a collaborative agreement between boeing and NASA. Under the SAA, boeing will furnish the HWB model and NASA will facilitate the 14X22 wind tunnel for two experiment test campaigns. In addition, NASA will furnish a set of turbine-powered simulator systems for the tests. 2.0 scope & objective(s): the scope of this task order is to develop detailed test requirements and perform computational analysis for experiment development for a subscale wind tunnel experiment with two test campaigns that NASA and boeing will conduct under the SAA1-1018, annex 7. These tests are required to understand operability issues that might result from the PAI of an uhbr engine on a low-noise HWB advanced vehicle configuration as well as the low speed performance resulting from such integration. The two test campaigns are described as follows: flow-thru nacelle (FTN) and ejector test campaign: an engine airframe operability test at key low speed operating conditions for the measurement and characterization of inlet flow distortion and