Extensions to conventional aircraft aerodynamic models are required to adequately predict responses when nonlinear unsteady flight regimes are encountered, especially at high incidence angles and under maneuvering conditions. For a number of reasons, such as loss of control, both military and civilian aircraft may extend beyond normal and benign aerodynamic flight conditions. In addition, military applications may require controlled flight beyond the normal envelope, and civilian flight may require adequate recovery or prevention methods from these adverse conditions. These requirements have led to the development of more general aerodynamic modeling methods and provided impetus for researchers to improve both techniques and the degree of collaboration between analytical and experimental research efforts. In addition to more general mathematical model structures, dynamic test methods have been designed to provide sufficient information to allow model identification. This paper summarizes research to develop a modeling methodology appropriate for modeling aircraft aerodynamics that include nonlinear unsteady behaviors using both experimental and computational test methods. This work was done at Langley Research Center, primarily under the NASA Aviation Safety Program, to address aircraft loss of control, prevention, and recovery aerodynamics.
Nonlinear Unsteady Aerodynamic Modeling Using Wind Tunnel and Computational Data
AIAA SciTech Conference ; 2016 ; San Diego, CA, United States
04.01.2016
Aufsatz (Konferenz)
Keine Angabe
Englisch
Nonlinear Unsteady Aerodynamic Modeling Using Wind-Tunnel and Computational Data
Online Contents | 2016
|Nonlinear Unsteady Aerodynamic Modeling Using Wind-Tunnel and Computational Data
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