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Wind Tunnel Comparison of Flapped and FishBAC Camber Variation for Lift Control

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

Original languageEnglish
Title of host publicationAIAA Scitech 2020 Forum
Publisher or commissioning bodyAmerican Institute of Aeronautics and Astronautics Inc. (AIAA)
DateAccepted/In press - 30 Aug 2019
EventAIAA SciTech Forum 2020 - Hyatt Regency Orlando, Orlando, United States
Duration: 6 Jan 202010 Jan 2020

Conference

ConferenceAIAA SciTech Forum 2020
CountryUnited States
CityOrlando
Period6/01/2010/01/20

Abstract

Unlike hinged flaps (e.g. ailerons, elevator and rudder), camber morphing devices vary camber distribution in a smooth and continuous way, resulting on aerodynamic efficiency improvements due to the absence of surface discontinuities. One such camber morphing concept, the Fish Bone Active Camber (FishBAC) device, has shown significant aerodynamic benefits when compared to a flap. A 2D wind tunnel tes twas performed to further investigate the FishBAC’s behavior in terms of its aerodynamic performance and the size and structure of the shed wake. To establish a direct comparison, a hinged flap was also tested under equivalent flow conditions. A combination of quasi-steady force balance and wake rake pressure measurements were used to determine aerodynamic force coefficients. Additionally, these measurements are complemented by a flow visualization study performed using Particle Image Velocimetry, where a visual comparison on the size and vortical structure of the near field wakes was conducted. Results show that the FishBAC achieves at least 16% higher aerodynamic efficiency than the flap.

Event

AIAA SciTech Forum 2020

Duration6 Jan 202010 Jan 2020
Location of eventHyatt Regency Orlando
CityOrlando
CountryUnited States
Degree of recognitionInternational event

Event: Conference

Documents

Documents

  • Full-text PDF (accepted author manuscript)

    Rights statement: This is the author accepted manuscript (AAM). The final published version (version of record) is available online via American Institute of Aeronautics and Astronautics at [insert hyperlink] . Please refer to any applicable terms of use of the publisher.

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    Embargo ends: 1/01/99

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