High-lift simulations of slotted, natural-laminar-flow airfoils with drooped leading edge

Hector D. Ortiz-Melendez, Ethan Long, George Toth, Kathryn Keely, James G. Coder

Research output: Chapter in Book/Report/Conference proceedingConference contribution

3 Scopus citations


A computational study was performed to determine the optimal drooped leading edge configuration for a high-lift system compatible with a slotted, natural-laminar-flow airfoil specially designed for a commercial transport. Morphing technology was applied to mitigate abrupt wing-stall characteristics by increasing the radius and bluntness of the main-element’s leading edge. As a result, significantly higher overall maximum lift coefficients were obtained. A previous aft-element optimization for an SNLF airfoil designed for business jets, referred to in this paper as non-optimized, was found to be unsuitable for the system studied herein due to high-lift results showing significant signs of wake bursting. A constant slot-width proved beneficial for a high-lift configuration using morphing technology. Detrimental pressure peaks caused by the sharp curvature of the flap-like drooped leading edge’s upper surface led to compressible stall. This insight on why morphing technology has a superior performance was provided by surface pressure distributions.

Original languageEnglish (US)
Title of host publicationAIAA Scitech 2020 Forum
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
Number of pages31
ISBN (Print)9781624105951
StatePublished - 2020
EventAIAA Scitech Forum, 2020 - Orlando, United States
Duration: Jan 6 2020Jan 10 2020

Publication series

NameAIAA Scitech 2020 Forum
Volume1 PartF


ConferenceAIAA Scitech Forum, 2020
Country/TerritoryUnited States

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering


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