Simultaneous flow field investigation and force/moment measurements of a generic blown wing with control surface

M. Bronz, E. Aydin, I. Fenercioglu, O. Cetiner

Research output: Chapter in Book/Conference proceeding with ISSN or ISBNConference contribution with ISSN or ISBN

Abstract

A generic rectangular blown wing model (17.8 cm chord, and 45 cm span) that can rotate 360 along spanwise axis equipped with a control surface and a propeller is studied experimentally to define the optimum propeller position to recover the generation of pitching moment. Particular interest is given to the moment generation capability at high angles of attack with big flap deflections. A flap is placed in the mid-section of the wing, submerged in the propeller slipstream. Flow separation around the wing model is investigated using Digital Particle Image Velocimetry (DPIV) method with simultaneous force and moment measurements. The blown wing is considered both at static angles of attack and in a transition from 0 to 90 , and 90 to 0 . The results provide a better understanding of the lift-drag-moment equilibrium, flow separation from the upper surface of the wing and the flap, and additionally the control reversal limits during reverse flow.

Original languageEnglish
Title of host publicationAIAA Scitech 2019 Forum
ISBN (Electronic)9781624105784
DOIs
Publication statusPublished - 6 Jan 2019
EventAIAA Scitech 2019 Forum - San Diego, United States
Duration: 7 Jan 201911 Jan 2019

Publication series

NameAIAA Scitech 2019 Forum

Conference

ConferenceAIAA Scitech 2019 Forum
CountryUnited States
CitySan Diego
Period7/01/1911/01/19

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