151. A study of the unsteady aerodynamics of a wing at high angles of attack using decambering to model separated flow
- Author
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B Antony Samuel and Rinku Mukherjee
- Subjects
Physics ,020301 aerospace & aeronautics ,Multidisciplinary ,Wing ,Angle of attack ,Solution state ,Flow (psychology) ,Decambering ,02 engineering and technology ,Mechanics ,Aerodynamics ,01 natural sciences ,010305 fluids & plasmas ,0203 mechanical engineering ,0103 physical sciences ,Transient (oscillation) ,Vortex lattice method - Abstract
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 $$C_L(t)$$ 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.
- Published
- 2018
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