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Analysis of the dynamic stability derivatives for high angle of attack aircraft
Modern, high performance aircraft are required to be able
to fly and be controlled over a wide variety of flight conditions.
In order to predict the aircraft behavior and control
requirements over the entire flight regime it is necessary
to have a proper aerodynamic model. Flight conditions
at high angles of attack lead to separated flows making the
aerodynamic model more difficult to obtain. In this research
wind tunnel experiments are performed on an F-5 air-
craft model at high angles of attack, with small oscillations
about the body oriented roll axis. In addition the
free stream environment can be configured in one of three
ways: l) straight uniform flow, 2) curved flow to simulated
a horizontal turn, and 3) rolling flow to simulated a roll
motion about the relative Velocity vector.