Advanced Ducted Propfan Analysis Code (ADPAC)
Introduction
The ADPAC code was developed by the Allison Engine Company under contracts
from NASA GRC to solve the tightly coupled internal+external flows through
future concept short duct turbofan engines. Features of the code are in
this file: intro.pdf. Examples of the range of
problems solved with ADPAC are shown as thumbnail images in: thumb.pdf
Code Distribution
The ADPAC code is still under development and is designated as export controlled
under EAR - ECCN 9E003.b.2. ADPAC is not currently available for general
release. U.S. citizens who represent Government organizations, U.S. aircraft
industry or domestic entities may request the code. To request the code,
start at the Commercial Technology Office's
software page.
Version:
User's Manual
Reports
The file papers.htm
lists several reports containing application and verification of ADPAC.
Also useful is the final report from Task 7 with information on running
the code with the implicit solver:
http://gltrs.grc.nasa.gov/reports/1996/CR-195468.pdf
A limited number of hard copies are available from Christopher.J.Miller@nasa.gov.
Job Sizing
Note: a single blade passage requires at least 250,000 grid points, and
will run in 128MB of RAM. If you are using multigrid, the coarser grid levels
are internally generated and count against the estimate above.
Storage: Files are stored as 32bit reals, so
-
mesh storage is (# grid pts)*(4 bytes/real)*(3 coordinates)
-
flow (plot3d) storage is (# grid pts)*(4 bytes/real)*(5 variables)*(2:relative
+ absolute frames)
-
restart storage is (# grid pts)*(4 bytes/real)*(6 variables; if using B.L.
turbulence model)
If you use the one or two equation models the restart storage goes up plus
you can write out turbulence info. to look at later, etc.
CPU Time depends on convergence level. Convergence
(three orders of residual reduction) can be obtained in roughly ...
-
500 cycles on a smooth grid with multigrid,
using wall functions and if not near stall, or
-
2000 cycles if near stall and/or resolving a boundary layer.
-
On 3.2GHz Xeon cpu, you should figure roughly 10 microseconds per iteration
per grid point.
Sample Cases
A number of sample cases are included in the distribution, see the sample
cases page to check the version and download them. You can also download all of them in a single
52MB sample.tar file.
Newly added (and under construction):
-
box - Inviscid flow in a box. The simplest test
case.
-
7 Oct 1999 - Updated the documentation. [box.tar.Z
(~200KB)]
-
box-v - Viscous flow in a box. A not-so-simple
test case.
-
7 Oct 1999 - Updated the documentation. [box-v.tar.Z
(~3.4MB)]
-
flatplate - development of a turbulent boundary layer
-
markii - The Mark II turbine vane heat transfer
problem.
-
1 Oct 1999 - Updated the .input file, added sample output - cjm. [markii.tar.Z
(~336 KB)]
-
nasa - The NASA 1.15 pressure ratio fan. [nasa.tar.Z
(~1.5MB)]
-
airfoil.2d - An example of how to run a
2D airfoil. [airfoil.2d.tar.Z (~0.15MB)]
-
rotor67 - The NASA Lewis (now Glenn) "Rotor
67". [rotor67.tar.Z (~0.18MB)]
-
stage37 - The NASA Lewis (now Glenn) "Stage
37" set up as a coarse grid inviscid problem for steady or unsteady solution.
-
6 Oct 1999 - Fixed bad mesh file and added sample output -cjm. [stage37.tar.Z
(~1.5MB)]
-
wedge - (6/14/99) 2D supersonic flow
over a wedge or through an inlet like geometry. [wedge.tar.Z
(~0.5MB)]
Note: all user's are required by the Use Agreement to provide feedback on their experiences
(+ and -) with the code. Please send comments to
Christopher.J.Miller@nasa.gov
Thanks!
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Updated:
Fri Jun 9 08:49:15 EDT 2006