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A study of the unsteady aerodynamics of a wing at high angles of attack using decambering to model separated flow
B. Antony Samuel,
Published in Springer
Volume: 43
Issue: 8
An Unsteady Vortex Lattice Method is developed and validated. It is coupled with a decambering methodology to account for viscous effects on the aerodynamic coefficients. Two additional methodologies to select a unique solution when multiple solutions arise have been proposed. The transient nature of the aerodynamic loads of a suddenly moving wing at different angles of attack is examined. Sudden jumps are observed in the CL(t) at post-stall angles of attack. The jumps are followed by the presence of asymmetric solutions, which then decline with time and a change in the solution state. Higher angles of attack see an increasing number of jumps. © 2018, Indian Academy of Sciences.
About the journal
JournalData powered by TypesetSadhana - Academy Proceedings in Engineering Sciences
PublisherData powered by TypesetSpringer
Open AccessNo
Concepts (9)
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    Aerodynamic stalling
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    High angle of attack
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    Separated flows
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    Angle of attack