Next Generation Civil Transport Aircraft Design Considerations for Improving Vehicle and System-Level Efficiency

Acosta, Diana; Guynn, Mark D.; Wahls, Richard A.; DelRosario, Ruben

doi:10.2514/6.2013-4286

Cited by 3 publications

(2 citation statements)

References 20 publications

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“…Aircraft design and air traffic management influence each other. Acosta et al [6] described that how operational constraints of air transportation would lead to changes in the aircraft design. More specifically, the Next Generation Air Transportation System (NextGen) improves the airspace network by reducing delay time and improves fuel efficiency along the aircraft's flight path, thus reducing the operating weight of the aircraft.…”

Section: Literature Reviewmentioning

confidence: 99%

Data-driven Operation-based Aircraft Design Optimization

Kim

Druot

Liem

2020

Aiaa Aviation 2020 Forum

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In this work, we integrate a mission analysis algorithm into the Multidisciplinary Airplane Research Integrated Library (MARILib), which is a multidisciplinary optimization tool for aircraft sizing. The main purpose of such an integration is to include aircraft operational data from the initial design process, to develop a more realistic aircraft design framework. With this approach, the design and mission requirements that reflect how aircraft actually operate are considered in the design process. Mission analysis tools are developed to model realistic aircraft operations. Data analytics, including clustering algorithms, is performed to extract information from flight data, which then becomes input to MARILib. The aim of the framework is to reduce operational costs of aircraft starting from the initial design itself, by incorporating air transportation data into the conceptual design stages.

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Section: Literature Reviewmentioning

confidence: 99%

Data-driven Operation-based Aircraft Design Optimization

Kim

Druot

Liem

2020

Aiaa Aviation 2020 Forum

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“…Future civil subsonic transport aircraft designs and research are aimed at improving aerodynamic efficiency and reducing environmental impacts. 3 The aerodynamic efficiency is expressed by the lift-to-drag ratio (L/D) and increases to this ratio can be achieved through reductions in drag. Since the majority of a subsonic commercial transports' flight profile is in the cruise portion, a reduction in the cruise drag can lead to a decrease in the airplane gross weight and thereby a reduction in its fuel consumption.…”

mentioning

confidence: 99%

Mach Stability Improvements Using an Existing Second Throat Capability at the National Transonic Facility (Invited)

Chan

Balakrishna

Walker

et al. 2015

53rd AIAA Aerospace Sciences Meeting

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Recent data quality improvements at the National Transonic Facility (NTF) have an intended goal of reducing the Mach number variation in a data point to within ±0.0005, with the ultimate goal of reducing the data repeatability of the drag coefficient for full-span subsonic transport models at transonic speeds to within half a drag count. This paper will discuss the Mach stability improvements achieved through the use of an existing second throat capability at the NTF to create a minimum area at the end of the test section. These improvements were demonstrated using both the NASA Common Research Model and the NTF Pathfinder-I model in recent experiments. Sonic conditions at the throat were verified using sidewall static pressure data. The Mach variation levels from both experiments in the baseline tunnel configuration and the choked tunnel configuration will be presented and the correlation between Mach number and drag will also be examined. Finally, a brief discussion is given on the consequences of using the second throat in its location at the end of the test section.

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Transonic Semispan Aerodynamic Testing of the Hybrid Wing Body with Over Wing Nacelles in the National Transonic Facility

Chan

Hooker

Wick

et al. 2017

55th AIAA Aerospace Sciences Meeting

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A wind tunnel investigation of a 0.04-scale model of the Lockheed Martin Hybrid Wing Body (HWB) with Over Wing Nacelles (OWN) air mobility transport configuration was conducted in the National Transonic Facility at the NASA Langley Research Center under a collaborative partnership between NASA, the Air Force Research Laboratory, and Lockheed Martin Aeronautics Company. The wind tunnel test sought to validate the transonic aerodynamic performance of the HWB and to validate the efficiency benefits of the OWN installation as compared to the traditional under-wing installation. The semispan HWB model was tested in a clean wing configuration and also tested with two different nacelles representative of a modern turbofan engine and a future advanced high bypass ratio engine. The nacelles were installed in three different locations with two over-wing positions and one under-wing position. Five-component force and moment data, surface static pressure data, and aeroelastic deformation data were acquired. For the cruise configuration, the model was tested in an angle-of-attack range between -2 and 10 degrees at free-stream Mach numbers from 0.3 to 0.9 and at unit Reynolds numbers between 8 and 39 million per foot, achieving a maximum of 80% of flight Reynolds numbers across the Mach number range. The test results validated pretest computational fluid dynamic (CFD) simulations of the HWB performance including the OWN benefit and the results also exhibited excellent transonic drag data repeatability to within ±1 drag count. This paper details the experimental setup and model overview, presents some sample data results, and describes the facility improvements that led to the success of the test.

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Next Generation Civil Transport Aircraft Design Considerations for Improving Vehicle and System-Level Efficiency

Cited by 3 publications

References 20 publications

Data-driven Operation-based Aircraft Design Optimization

Data-driven Operation-based Aircraft Design Optimization

Mach Stability Improvements Using an Existing Second Throat Capability at the National Transonic Facility (Invited)

Transonic Semispan Aerodynamic Testing of the Hybrid Wing Body with Over Wing Nacelles in the National Transonic Facility

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