Aerodynamic analysis of flapped airfoil at high angles of attack

Isham Shehata, Mohamed Y. Zakaria, Ahmed Hussein, Muhammad R. Hajj

Research output: Chapter in Book/Report/Conference proceedingConference contributionpeer-review

15 Scopus citations

Abstract

The use of oscillatory actuation of the trailing edge for a rigid airfoil as a potential mechanism for control or performance improvement of flying vehicles was investigated. Aerodynamic analysis involved performing a wind tunnel testing of a NACA 0012 wing spanning the total width of the test section. The measurements were conducted at a Reynolds numbers of 21 x 103. The trailing edge of the airfoil is hinged at 75% of the chord length from the leading edge allowing dynamic variations in the effective angle of attack through various flapping rates. For each value of the static mean angle of attack of the airfoil section, the trailing edge flap motion is performed with a fixed airfoil angle amplitudes of 0 and 10 degrees. The objective is to assess the effects of the effective angle of attack caused by the flap deflection on the flow dynamics, and provide data to compare with Leishman’s analytical model at different flap reduced frequencies. Results show good agreement with Leishman’s model at a lower amplitudes and frequency of oscillations, but larger discrepancies at higher amplitudes and frequency of oscillations were observed.

Original languageEnglish
Title of host publicationAIAA Aerospace Sciences Meeting
DOIs
StatePublished - 2018
EventAIAA Aerospace Sciences Meeting, 2018 - Kissimmee, United States
Duration: 8 Jan 201812 Jan 2018

Publication series

NameAIAA Aerospace Sciences Meeting, 2018

Conference

ConferenceAIAA Aerospace Sciences Meeting, 2018
Country/TerritoryUnited States
CityKissimmee
Period8/01/1812/01/18

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