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dc.contributor.authorMavris, Dimitri N.
dc.contributor.authorAhuja, Jai
dc.contributor.authorRenganathan, S. Ashwin
dc.date.accessioned2022-06-18T06:04:09Z
dc.date.available2022-06-18T06:04:09Z
dc.date.issued2022-06-09
dc.identifier.citationAhuja, Jai, Renganathan, S. Ashwin & Mavris, Dimitri N.(2022). Sensitivity Analysis of the Overwing Nacelle Design Space. Journal of Aircraft. https://doi.org/10.2514/1.C036687en_US
dc.identifier.urihttp://hdl.handle.net/1853/66805
dc.descriptionCopyright © 2022 by Jai Ahuja, S. Ashwin Renganathan, and Dimitri N. Mavris. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission.en_US
dc.descriptionPresented in part as Paper 2018-1757 at the AIAA SciTech 2018 Forum, Kissimmee, Florida, January 08–12 20en_US
dc.descriptionDOI: https://doi.org/10.2514/1.C036687en_US
dc.description.abstractThe overwing nacelle (OWN) concept refers to aircraft designs where the engine is installed above the wing. The OWN configuration offers several advantages over conventional underwing nacelle (UWN) vehicles, which include improved fuel burn and propulsive efficiencies due to the feasibility of ultra high bypass ratio turbofans, and reduced noise. However, a non-optimal OWN design can result in large transonic drag penalties that can potentially outweigh the aforementioned benefits. We study the OWN design problem from an aerodynamics and propulsion perspective, using the NASA common research model, a notional 90,000 pound thrust class turbofan model, and Reynolds–Averaged Navier-Stokes simulations. We first quantify the sensitivity of drag, lift, and pressure recovery to variations in engine location and power setting, and identify trends. Then, we perform aerodynamic design optimization of the wing and nacelle to determine OWN performance improvement from outer mold line refinement at a favorable engine installation location. A 20% reduction in drag is achieved for the optimized OWN configuration, highlighting the sensitivity of OWN aerodynamics to airframe contours. However, compared to the UWN baseline, the optimized OWN drag is 5% higher at the same lift and worsens significantly at higher lift.en_US
dc.description.sponsorshipAirbusen_US
dc.language.isoen_USen_US
dc.publisherGeorgia Institute of Technologyen_US
dc.relation.ispartofseriesASDL ;
dc.subjectOverwing nacelleen_US
dc.subjectPropulsion-airframe integrationen_US
dc.subjectOptimizationen_US
dc.titleSensitivity Analysis of the Overwing Nacelle Design Spaceen_US
dc.typePost-printen_US
dc.contributor.corporatenameGeorgia Institute of Technology. School of Aerospace Engineeringen_US
dc.contributor.corporatenameGeorgia Institute of Technology. Aerospace Systems Design Laboratoryen_US
dc.publisher.originalAmerican Institute of Aeronautics and Astronauticsen_US
dc.identifier.doihttps://doi.org/10.2514/1.C036687en_US


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