TY - GEN
T1 - Aerodynamic analysis of flapped airfoil at high angles of attack
AU - Shehata, Isham
AU - Zakaria, Mohamed Y.
AU - Hussein, Ahmed
AU - Hajj, Muhammad R.
N1 - Publisher Copyright:
© 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2018
Y1 - 2018
N2 - 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.
AB - 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.
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U2 - 10.2514/6.2018-0037
DO - 10.2514/6.2018-0037
M3 - Conference contribution
AN - SCOPUS:85141592325
SN - 9781624105241
T3 - AIAA Aerospace Sciences Meeting, 2018
BT - AIAA Aerospace Sciences Meeting
T2 - AIAA Aerospace Sciences Meeting, 2018
Y2 - 8 January 2018 through 12 January 2018
ER -