A computational procedure has been developed for predicting the time dependent longitudinal and lateral aerodynamic characteristics of wing-body configurations at angles of attack up to and beyond stall. The purpose of the procedure is to provide the aircraft designer with a tool for simulating and alleviating such adverse wing stalling characteristics as wing rock, wing drop, loss of roll control or roll control reversal, etc. and thereby lead to the design of aircraft with improved stall, departure and spin resistance characteristics. The procedure is based on nonlinear lifting line theory which has been modified to include unsteady wake effects.
Nonlinear Lifting Line Theory for Predicting Stalling Instabilities on Wings of Moderate Aspect Ratio
1976
97 pages
Report
Keine Angabe
Englisch
Aerodynamics , Fluid Mechanics , Lifting surfaces , Wing body configurations , Angle of attack , Aerodynamic characteristics , Mathematical prediction , Theory , Computations , Methodology , Nonlinear systems , Stalling , Nonuniform flow , Time dependence , Hysteresis , Structural engineering , Handbooks , Wake , Instability , Aspect ratio , Design , Spin resistance , Lifting line theory
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