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Full potential unsteady computations including aeroelastic effectsA unified formulation is presented based on the full potential framework coupled with an appropriate structural model to compute steady and unsteady flows over rigid and flexible configurations across the Mach number range. The unsteady form of the full potential equation in conservation form is solved using an implicit scheme maintaining time accuracy through internal Newton iterations. A flux biasing procedure based on the unsteady sonic reference conditions is implemented to compute hyperbolic regions with moving sonic and shock surfaces. The wake behind a trailing edge is modeled using a mathematical cut across which the pressure is satisfied to be continuous by solving an appropriate vorticity convection equation. An aeroelastic model based on the generalized modal deflection approach interacts with the nonlinear aerodynamics and includes both static as well as dynamic structural analyses capability. Results are presented for rigid and flexible configurations at different Mach numbers ranging from subsonic to supersonic conditions. The dynamic response of a flexible wing below and above its flutter point is demonstrated.
Document ID
19890009872
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Shankar, Vijaya (Rockwell International Corp. Thousand Oaks, CA., United States)
Ide, Hiroshi (Rockwell International Corp. Los Angeles, CA., United States)
Date Acquired
September 5, 2013
Publication Date
February 1, 1989
Publication Information
Publication: NASA, Langley Research Center, Transonic Unsteady Aerodynamics and Aeroelasticity 1987, Part 1
Subject Category
Aerodynamics
Accession Number
89N19243
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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