Adding a Reproducible Airplane Model to the Austin RCS Benchmark Suite

2021 ◽  
Vol 35 (11) ◽  
pp. 1408-1409
Author(s):  
Jon Kelley ◽  
Andrew Maicke ◽  
David Chamulak ◽  
Clifton Courtney ◽  
Ali Yilmaz
Keyword(s):  
Cross Section ◽  
Material Properties ◽  
Reference Data ◽  
Scale Model ◽  
Benchmark Problems ◽  
Surface Integral ◽  
Exterior Surface ◽  
Surface Integral Equation ◽  
File Formats ◽  
Benchmark Suite

A full-size airplane model (the EXPEDITE-RCS model) was developed as part of a benchmark suite for evaluating radar-cross-section (RCS) prediction methods. To generate accurate reference data for the benchmark problems formulated using the model, scale-model targets were additively manufactured, their material properties and RCS were measured, and the measurements were validated with a surface-integral-equation solver. To enable benchmarking of as many computational methods as possible, the following data are made available in a version-controlled online repository: (1) Exterior surface (outer mold line) of the CAD model in two standard file formats. (2) Triangular surface meshes. (3) Measured and predicted monostatic RCS data.

scholarly journals Accuracy of surface integral equation matrix elements in plasmonic calculations

2015 ◽  
Vol 32 (3) ◽  
pp. 485 ◽  
Author(s):  
T. V. Raziman ◽  
W. R. C. Somerville ◽  
O. J. F. Martin ◽  
E. C. Le Ru
Keyword(s):  
Integral Equation ◽  
Matrix Elements ◽  
Surface Integral ◽  
Surface Integral Equation

The Unsteady Loading on a Marine Propeller in a Nonuniform Flow

1964 ◽  
Vol 8 (05) ◽  
pp. 29-38
Author(s):  
Michael D. Greenberg
Keyword(s):  
Free Stream ◽  
Marine Propeller ◽  
Nonuniform Flow ◽  
Surface Integral ◽  
Practical Applications ◽  
Vortex Model ◽  
Surface Integral Equation ◽  
Lifting Surface ◽  
Finite Wing ◽  
Unsteady Loading

The lifting-surface integral equation governing the unsteady loading on a marine propeller in a nonuniform free stream is derived using a classical vortex model. The induced downwash is split into a part corresponding to a locally tangent flat finite wing and wake, plus parts corresponding to the effects of the "helicoidal deviation" from this, of the true blade and wake, and the interference from the other blades and their wakes. Strip-type approximations are tolerated on these terms while a lifting-surface formulation is retained for the dominant finite flat-wing portion. A simple numerical example is carried out and these effects are indeed found to be quite small; so small, in fact, that it may suffice to retain only the flat finite-wing terms in practical applications.

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