TY - GEN
T1 - Aerodynamic response of a naca-0012 airfoil undergoing non-sinusoidal pitching waveforms
AU - Shehata, Hisham M.
AU - Zakaria, Mohamed Y.
AU - Hajj, Muhammad R.
AU - Woolsey, Craig A.
N1 - Publisher Copyright:
© 2019, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2019
Y1 - 2019
N2 - The aerodynamic responses of a NACA-0012 airfoil undergoing different pitching waveforms are investigated experimentally. Four different pure pitching trajectories including sinusoidal, trapezoidal, sawtooth and reverse sawtooth waveforms are considered. The airfoil is set at mean angles of attack (AoA) of α0= 3.5◦, 7◦, and 12◦with a waveform pitching amplitude of αA= 3.5◦. Reduced frequencies are varied from k = 0.025 to 0.140. The free stream velocity is set to 4.7 m/s, which yielded a chord Reynolds number of Re = 2.1 x 104. Static lift and drag coefficients are measured prior to running the unsteady experiments to establish a baseline for comparison. The objective of the experiment is to assess the lift production as a result of the time-varying airfoil motion, and to compare the measured unsteady aerodynamic response against quasi-steady and unsteady state-space models. Experimental results show that a trapezoidal waveform provides the most significant gain in the lift amplitude followed by the reverse sawtooth waveform. Other waveforms experienced slightly larger lift deficiency factor as a result of experiencing different flow circulation at the wake of their respective motion.
AB - The aerodynamic responses of a NACA-0012 airfoil undergoing different pitching waveforms are investigated experimentally. Four different pure pitching trajectories including sinusoidal, trapezoidal, sawtooth and reverse sawtooth waveforms are considered. The airfoil is set at mean angles of attack (AoA) of α0= 3.5◦, 7◦, and 12◦with a waveform pitching amplitude of αA= 3.5◦. Reduced frequencies are varied from k = 0.025 to 0.140. The free stream velocity is set to 4.7 m/s, which yielded a chord Reynolds number of Re = 2.1 x 104. Static lift and drag coefficients are measured prior to running the unsteady experiments to establish a baseline for comparison. The objective of the experiment is to assess the lift production as a result of the time-varying airfoil motion, and to compare the measured unsteady aerodynamic response against quasi-steady and unsteady state-space models. Experimental results show that a trapezoidal waveform provides the most significant gain in the lift amplitude followed by the reverse sawtooth waveform. Other waveforms experienced slightly larger lift deficiency factor as a result of experiencing different flow circulation at the wake of their respective motion.
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U2 - 10.2514/6.2019-0303
DO - 10.2514/6.2019-0303
M3 - Conference contribution
AN - SCOPUS:85083942544
SN - 9781624105784
T3 - AIAA Scitech 2019 Forum
BT - AIAA Scitech 2019 Forum
T2 - AIAA Scitech Forum, 2019
Y2 - 7 January 2019 through 11 January 2019
ER -