TY - GEN
T1 - Geometrically-exact extension of theodorsen’s frequency response model
AU - Taha, Haithem E.
AU - Yan, Zhimiao
AU - Hajj, Muhammad R.
N1 - Publisher Copyright:
© 2015 by Haithem E Taha. Published by the American Institute of Aeronautics and Astronautics, Inc.
PY - 2015
Y1 - 2015
N2 - The classical unsteady theory of Theodorsen is revisited relaxing some of the major assumptions such as (1) flat wake, (2) small angle of attack, (3) small disturbances to the mean flow components, and (4) time-invariant free-stream. A semi-analytical, geometrically- exact, unsteady potential flow model is developed for airfoils undergoing large amplitude maneuvers. The numerical implementation of the developed model is presented. The unsteady predictions of the developed model are validated against experimental and computational results. Then, the frequency response of the flow dynamics is determined at different angles of attack. While good agreement is shown with Theodorsen’s function at small angle of attack, considerable qualitative and quantitative discrepancies between the obtained frequency response at large angles of attack and Theodorsen’s function are observed.
AB - The classical unsteady theory of Theodorsen is revisited relaxing some of the major assumptions such as (1) flat wake, (2) small angle of attack, (3) small disturbances to the mean flow components, and (4) time-invariant free-stream. A semi-analytical, geometrically- exact, unsteady potential flow model is developed for airfoils undergoing large amplitude maneuvers. The numerical implementation of the developed model is presented. The unsteady predictions of the developed model are validated against experimental and computational results. Then, the frequency response of the flow dynamics is determined at different angles of attack. While good agreement is shown with Theodorsen’s function at small angle of attack, considerable qualitative and quantitative discrepancies between the obtained frequency response at large angles of attack and Theodorsen’s function are observed.
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U2 - 10.2514/6.2015-1502
DO - 10.2514/6.2015-1502
M3 - Conference contribution
AN - SCOPUS:84982983887
SN - 9781624103438
T3 - 53rd AIAA Aerospace Sciences Meeting
BT - 53rd AIAA Aerospace Sciences Meeting
T2 - 53rd AIAA Aerospace Sciences Meeting, 2015
Y2 - 5 January 2015 through 9 January 2015
ER -