Aircraft Stability Analysis Including Unsteady Aerodynamic Effects
Aircraft Stability Analysis Including Unsteady Aerodynamic Effects
Aircraft Stability Analysis Including Unsteady Aerodynamic Effects
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9140θ = 27 deg20φ, deg0-20-4015.6 15.8 16 16.2 16.4 16.6 16.8α, deg282624Left wingRight wing2215.6 15.8 16 16.2 16.4 16.6 16.8time, sFigure 3-13 Roll angle time history for θ 0 = 27 deg (above), and corresponding angleof attack time history for each half-wing (below).