Ko, Joon Soo2015-05-142015-05-141985http://hdl.handle.net/10919/52300Modern, 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.xxi, 161 leavesapplication/pdfen-USIn CopyrightLD5655.V856 1985.K646Stability of airplanesWind tunnelsAerodynamics -- Mathematical modelsDissertation