摘要: This report presents the results of the initial phase of a high angle-of-attack integrated parameter identification development program whose purpose is to develop the simulations, identification models, and flight test procedures... 展开 This report presents the results of the initial phase of a high angle-of-attack integrated parameter identification development program whose purpose is to develop the simulations, identification models, and flight test procedures which will offer improved accuracy in the determination of aerodynamic characteristics in the stall/post-stall flight regime. A review of high angle-of-attack aerodynamics, summarizes the complicated flow interactions which occur in the stall/post-stall flight regime and isolates important phenomena that should be simulated. Motions such as 'pitch up', 'wing rock' and 'yaw departure' characterize such incipient spin conditions. A summary of analysis, wind tunnel and flight testing experience in the high angle-of-attack regime is also presented. The major sections of this report describe a six-degree-of-freedom computer program which this firm has been developed as the first step in the integrated identification procedure. This program will be used to simulate flight test data, to compare with simplified identification models, and for the overall development of the high angle-of-attack identification procedures. 收起