Task title: commercial cargo derivative study of the advanced hybrid wing body configuration with over wing engine nacelles as part of the NASA advanced air vehicles program, the advanced air…

This is a task order awarded by the National Aeronautics and Space Administration (NASA) Langley Research Center to Lockheed Martin Corporation, doing business as Lockheed Martin Aeronautics Company, under a non-reimbursable interagency agreement with the U.S. Air Force Research Laboratory (AFRL). The task order is for the design of a commercial air cargo variant of the Advanced Hybrid Wing Body (AHWB) aircraft configuration with over-wing engine nacelles, as part of NASA's Advanced Air Transport Technology (AATT) project. The goal is to evaluate the potential benefits of this concept for commercial freighter applications, including reductions in aircraft fuel consumption, nitrogen oxide (NOx) emissions, and noise, compared to existing commercial freighter aircraft. The task order has a ceiling value of $543,539.00 and does not have a set-aside designation.

Task title: commercial cargo derivative study of the advanced hybrid wing body configuration with over wing engine nacelles as part of the NASA advanced air vehicles program, the advanced air transport technology (aatt) project is performing research into concepts, technologies, and tools that will enable dramatic reductions in noise and emissions, and increase the performance (fuel burn and reduced field length) characteristics of subsonic/transonic fixed wing aircraft. The aatt project pursues a multi-generational approach addressing the needs of today but with an emphasis on establishing the technological foundations necessary to enable the capabilities needed in the decades ahead. The system level metrics and goals for a future subsonic transport as provided by the aatt project are shown below in table 1. The noise metric/goal is expressed as a cumulative margin relative to the icao stage 4 noise regulations and is given in units of effective perceived noise in decibels (epndb). The cumulative margin is a SUM of the differences between the predicted noise levels of an aircraft and the certification limit at each of the three measurement points (approach, sideline, and flyover). The LTO NOX emissions metric/goal is expressed as a percentage difference relative to the caep tier 6 NOX emissions regulation. The tier 6 regulations are a function of engine overall pressure ratio and overall rated thrust and are measured in grams of NOX emissions per kilonewton of engine thrust (g / KN). The cruise NOX emissions metric/goal is expressed as a percentage difference relative to the NOX emissions from a n+0 aircraft baseline and is measured as pounds (LBM) of NOX emitted during cruise. The aircraft fuel consumption metric/goal is expressed as a percentage difference relative to the block fuel consumption of a n+0 aircraft baseline. The block fuel consumption is the total amount of fuel consumed for the aircraft mission and is measured in pounds (LBM) of fuel. In may 2014, the NASA aatt project entered into a non-reimbursable interagency agreement (IA1-1208, annex 6) with the air force research laboratory (afrl) to jointly test and evaluate the transonic cruise characteristics of an energy efficient advanced hybrid wing body (ahwb) aircraft configuration in the national transonic facility (NTF) at the NASA langley research center. The ahwb configuration was designed by lockheed martin (LM) under contract to afrl as part of the revolutionary configurations for energy efficiency (rcee) task that investigated future energy efficient air mobility military transport concepts for the air force. Some details of the design were publicly released and documented in aiaa-2014-1285. The ahwb configuration also fits well within the research efforts of aatts integrated boundary layer ingestion subproject and IT has the potential to significantly reduce aircraft fuel consumption, nitrous oxide (NOX) emissions, and noise concurrently. This may be accomplished with its advanced shape to reduce aircraft drag, efficient integration of advanced engines, and its over wing nacelle (own) propulsion integration scheme, which helps shield engine inlet noise while providing a powered lift benefit to reduce community noise footprint. This new task order is intended to develop a conceptual design of a commercial air cargo version of the ahwb with own configuration for a n+3 entry into service (EIS) in order to evaluate the potential benefits for commercial freighter applications. The design will examine and address aerodynamic performance, structural layout, and cargo handling for different sized variants of the design and quantify the potential reductions in aircraft fuel consumption, NOX emissions, and noise as compared to todays existing commercial freighters that are derivatives of commercial passenger airplanes.