Title
Development of an advanced panel method for complex configurations in subsonic compressible flow; Application to the computation of the potential flow through ducts.
Author
van Beek, C.M.
Institution
National Aerospace Laboratory NLR
Date
1987-11-19
Abstract
The application of a boundary integral or "panel" method to duct flows is described. The method is capable of computing the three dimensional, steady state, subsonic, linearized (Prandtl-Glauert) potential flow about general configurations. The method is characterized by the application of a Dirichlet boundary condition and of "compressible" source and doublet distributions which are directly applied in the physical space. The geometry of the non-branching duct (one inflow and one outflow cross-section) may be arbitrary as long as the requirements for using the Prandtl-Glauert equation are met. A description of the method is given and three examples of application are presented with emphasis on the investigation of the conservation of mass-flow through the ducts.
Subject
Subsonic flow
Panel method (Fluid Dynamics)
Compressible flow
Aerodynamic configurations
Ducts
Boundary value problems
Potential flow
Windtunnels
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Publisher
Nationaal Lucht- en Ruimtevaartlaboratorium
Access restriction
Campus only
Source
NLR-TR 88001 U
Part of collection
Aerospace Engineering Reports
Document type
report
Rights
(c)1987 National Aerospace Laboratory NLR