Difference between revisions of "Isotropic Mesh Generation"
From crtc.cs.odu.edu
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| − | :Element angle distribution (in 5-deg increments) of aircraft nacelle grids. | + | :Element angle distribution (in 5-deg increments) of aircraft nacelle grids. The dihedral angle extrema are reported for each method. |
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| − | :Element angle distribution (in 5-deg increments) after improvement of Rocket and Lv2b grids. | + | :Element angle distribution (in 5-deg increments) after improvement of Rocket and Lv2b grids. The dihedral angle extrema are reported for each method. |
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| − | :Slivers after the completion of refinement of the aircraft nacelle. | + | :Slivers after the completion of refinement of the aircraft nacelle. Red represents elements whose minimum dihedral angle is smaller than 2◦ or larger than 178◦. |
== aircraft pg. 140-142 == | == aircraft pg. 140-142 == | ||
Revision as of 13:05, 27 March 2018
Contents
Sphere and Two Blades with Merging Wakes and a Symmetry Plane
Cuts of tetrahedral grids of a sphere generated for varied cdfm ∈ [0, 1]. Blue
corresponds to larger values of the distribution function. Red corresponds to smaller values
of the distribution function.
Cuts of tetrahedral grids of two blades with merging wakes and a symmetry
plane enclosed in an outer boundary generated for varied cdfm ∈ [0, 1] (shown in
(c)-(f)).
The input surface is depicted in (a)-(b). The wake region is modeled as an embedded/
transparent delete surface.
Element angle distribution (in 5-deg increments) of grids of sphere, for varied
cdfm.
The dihedral angle extrema and the element count are reported for each grid.
Element angle distribution (in 5-deg increments) of grids of two blades with
merging wakes and a symmetry plane enclosed in an outer boundary, for varied cdfm.
The
dihedral angle extrema and the element count are reported for each grid.
nacelle, rocket, and lv2b pg. 122-124
- Surface grid of an aircraft nacelle with engine inside a section of wind tunnel.
- #points: 27184; #triangles: 54360
- Surface grid of a rocket with engine, nozzle and transparent internal data surfaces inside flow field.
- #points: 20228; #triangles: 40448
- Surface grid of a launch vehicle with solid boosters inside flow field (Lv2b).
- #points: 42020; #triangles: 84024
| Geometry | Software | cdfm | cdfn | mrecm | nqual | csmth | msmth | nsmth | angdfs | angqual | mdbs | |||||||||||
|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|
| Nacelle | CDT3D | 0.291 | 0.7 | 2 | 3 | 0.5 | 1 | 2 | 165° | 120° | 0 | |||||||||||
| AFLR | 0.50 | 0.7 | 2 | 3 | 0.5 | 1 | 2 | 165° | 120° | 0 | ||||||||||||
| Rocket | CDT3D | 0.20 | 0.7 | 2 | 3 | 0.5 | 1 | 2 | 165° | 120° | 0 | |||||||||||
| AFLR | 0.60 | 0.7 | 2 | 3 | 0.5 | 1 | 2 | 165° | 120° | 0 | ||||||||||||
| Lv2b | CDT3D | 0.234 | 0.7 | 2 | 3 | 0.5 | 1 | 2 | 165° | 120° | 0 | |||||||||||
| AFLR | 0.30 | 0.7 | 2 | 3 | 0.5 | 1 | 2 | 165° | 120° | 0 | ||||||||||||
| Case | Software | #Cores | %Slivers (w/o improv.) (x10-3) |
#Tets (w/ improv.)(M) |
Min/Max Angle (w/ improv.) (deg) |
Initial Grid (sec) |
Refinement (min) |
Improvement (min) |
Total (min) | |||||||||
|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|
| Nacelle | CDT3D | 1 | 3.74 | 43.65 | 13.57°/153.44° | 1.36 | 20.01 | 14.30 | 34.33 | |||||||||
| CDT3D | 12 | 3.70 | 42.85 | 12.06°/159.52° | 1.36 | 5.02 | 18.59 | 23.64 | ||||||||||
| AFLR | 1 | 2.97 | 43.16 | 7.00°/164.86° | 5.63 | 22.59 | 6.40 | 29.09 | ||||||||||
| Rocket | CDT3D | 1 | 2.96 | 118.41 | 9.39°/159.30° | 1.58 | 52.85 | 64.56 | 117.44 | |||||||||
| CDT3D | 12 | 2.95 | 119.06 | 9.21°/158.33° | 1.58 | 14.51 | 68.23 | 82.76 | ||||||||||
| AFLR | 1 | 3.05 | 123.13 | 5.58°/164.75° | 6.76 | 131.89 | 25.41 | 157.42 | ||||||||||
| Lv2b | CDT3D | 1 | 5.09 | 98.21 | 6.60°/159.68° | 5.45 | 41.57 | 94.63 | 136.29 | |||||||||
| CDT3D | 12 | 4.69 | 113.99 | 8.24°/158.59° | 5.45 | 12.92 | 62.36 | 75.37 | ||||||||||
| AFLR | 1 | 3.49 | 104.10 | 6.84°/164.88° | 16.97 | 98.24 | 18.51 | 117.03 | ||||||||||
more nacelle, rocket, and lv2b pg. 125-127
- Tetrahedral field cuts of the aircraft nacelle
- Detail views of tetrahedral field cuts of aircraft nacelle generated with CDT3D
- Tetrahedral field cuts of the rocket
- Tetrahedral field cuts of the Lv2b
- Element angle distribution (in 5-deg increments) of aircraft nacelle grids. The dihedral angle extrema are reported for each method.
- Element angle distribution (in 5-deg increments) after improvement of Rocket and Lv2b grids. The dihedral angle extrema are reported for each method.
- Slivers after the completion of refinement of the aircraft nacelle. Red represents elements whose minimum dihedral angle is smaller than 2◦ or larger than 178◦.
