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Inlet Flow Distortion in an Advanced Civil Transport Boundary Layer Ingesting Engine Installation

Author(s)
Hall, DK; Greitzer, EM; Uranga, A; Drela, M; Pandya, SA
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Article is made available in accordance with the publisher's policy and may be subject to US copyright law. Please refer to the publisher's site for terms of use.
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Abstract
<jats:title>Abstract</jats:title> <jats:p>This article presents first-of-a-kind measurements, and complementary computations, of the flow through the propulsion system of a boundary layer ingesting, twin-engine advanced civil transport aircraft configuration. The experiments were carried out in the NASA Langley 14- by 22-foot Subsonic Tunnel, using a 1:11 scale model of the D8 “double-bubble” aircraft with electric ducted fans providing propulsive power. Overall force and moment measurements and flow field surveys at the inlet and nozzle exit planes were obtained. The computations were carried out with the NASA OVERFLOW code. The measurements and computations were conducted for a range of aircraft angles of attack and propulsor powers representing operating points during the aircraft mission. Velocity and pressure distributions at the propulsor inlet and exit, and integral inlet distortion metrics, are presented to quantify the flow nonuniformity due to boundary layer ingestion. The distorted inflow exhibits qualitative and quantitative changes over the mission, from a unidirectional stratified stagnation pressure at cruise to a streamwise vortex structure at climb conditions. The computations capture these flow features and reveal the interactions between airframe and propulsor that create these three-dimensional flow variations.</jats:p>
Date issued
2022
URI
https://hdl.handle.net/1721.1/145337
Department
Massachusetts Institute of Technology. Department of Aeronautics and Astronautics
Journal
Journal of Turbomachinery
Publisher
ASME International
Citation
Hall, DK, Greitzer, EM, Uranga, A, Drela, M and Pandya, SA. 2022. "Inlet Flow Distortion in an Advanced Civil Transport Boundary Layer Ingesting Engine Installation." Journal of Turbomachinery, 144 (10).
Version: Final published version

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