AIAA CFD 5th Drag Prediction Workshop
June
2012, New Orleans, LA
10
December 2011
Note: The Configuration
Geometry, Test Cases, and Gridding Guidelines are current as of 10 December
2011, but are subject to changes as developments
require. Please check the
website periodically for updates http://aaac.larc.nasa.gov/tsab/cfdlarc/aiaa-dpw/,
and/or register with aiaadpw@gmail.com
to be notified directly.
1.
Grid Convergence
study
at Mach = 0.85, CL = 0.500 (±0.001)
- Grid
refinement series from the Common Grid Sequence consisting of at least four
grid levels (Coarse, Medium, Fine, Extra-Fine Grids). Target grids should range
from 3 to 50 million unknowns.
- Chord
Reynolds Number Rn = 5x106 based on cREF = 275.80 in
- Reference Temperature = 100¡F
- Moment reference center is xREF = 1325.90 in, zREF = 177.95 in
2.
Optional Grid
Convergence study using participant developed grids:
- All
participants are encouraged to build their own grids using Ôbest practiceÕ
techniques. IGES and CATIA models of the 1-g shape at the design point are
available for grid construction. A family of grid sizes should be developed in
the range described above suitable for Grid Convergence Study. All grids used
for results presented at the workshop must be submitted to the DPW Organizing
Committee to be made available to all interested parties. Results and grids
will be published electronically on the DPW website.
- Mach
= 0.85
- Drag
Polar for alpha = 2.50¡,
2.75¡, 3.00¡, 3.25¡, 3.50¡, 3.75¡, 4.00¡
- Medium
Grid used in Case 1 from the Common Grid Sequence or participant developed
grids
- Chord
Reynolds Number Rn = 5x106 based on cREF = 275.80 in
- Reference Temperature = 100¡F
Details for the following three cases are listed on the TMBWG
website: http://turbmodels.larc.nasa.gov/
For each case use the three finest supplied grids.
1.
2D Zero
Pressure Gradient Flat Plate: M = 0.20; ReL
= 5 x106; Tref = 540 R
2.
2D Bump-in-channel:
M = 0.20; ReL = 3 x 106; Tref = 540 R
3.
2D NACA
0012 Airfoil: M = 0.15; ReC = 6 x 106;
Tref = 540 R
Notes:
á
Common Research Model Reference Geometry:
o SREF=
594,720 in2 (4130 ft2)
o cREF=
275.80 in
o xREF=
1325.90 in
o zREF=
177.95
o AR= 9.0
á
Geometry
Reference:
o JC Vassberg,
MA DeHaan, SM Rivers, and RA Wahls,
ÒDevelopment of a Common Research Model for Applied CFD Validation Studies,Ó
AIAA Paper 2008-6919, AIAA Applied Aerodynamics Conference, Honolulu, HI, August, 2008.
á
Simulations are to be Òfree airÓ; no wind
tunnel walls or model support systems are to be included.
á
Boundary layer is to be fully turbulent for
Case 1 and Case 2.