NESC1023 PROGRAM-H.
PROGRAM-H, Analysis of Transonic Airfoils with Turbulent Boundary Layer Correlation
NAME OR DESIGNATION OF PROGRAM, COMPUTER, DESCRIPTION OF PROGRAM OR FUNCTION, METHOD OF SOLUTION, RESTRICTIONS ON THE COMPLEXITY OF THE PROBLEM, TYPICAL RUNNING TIME, UNUSUAL FEATURES OF THE PROGRAM, RELATED AND AUXILIARY PROGRAMS, STATUS, REFERENCES, MACHINE REQUIREMENTS, LANGUAGE, OPERATING SYSTEM UNDER WHICH PROGRAM IS EXECUTED, OTHER PROGRAMMING OR OPERATING INFORMATION OR RESTRICTIONS, NAME AND ESTABLISHMENT OF AUTHORS, MATERIAL, CATEGORIES
[ top ]
[ top ]
To submit a request, click below on the link of the version you wish to order.
Only liaison officers are authorised to submit online requests. Rules for requesters are
available here.
| Program name | Package id | Status | Status date |
|---|---|---|---|
| PROGRAM-H | NESC1023/01 | Tested | 01-AUG-1986 |
Machines used:
| Package ID | Orig. computer | Test computer |
|---|---|---|
| NESC1023/01 | CDC 6600 | CDC CYBER 740 |
[ top ]
[ top ]
4. METHOD OF SOLUTION
The analysis program with boundary layer correction is the solution of the finite difference representation of the compressible flow equations. The physical plane is mapped onto the unit circle where the difference scheme is solved using a discrete Poisson Solver for the elliptic part of the problem and a number of relaxation iterations for the entire grid. A turbulent boundary layer correction based on the work of Nash-MacDonald has been incorporated into the program. It is solved iteratively with the flow calculations.
The analysis program with boundary layer correction is the solution of the finite difference representation of the compressible flow equations. The physical plane is mapped onto the unit circle where the difference scheme is solved using a discrete Poisson Solver for the elliptic part of the problem and a number of relaxation iterations for the entire grid. A turbulent boundary layer correction based on the work of Nash-MacDonald has been incorporated into the program. It is solved iteratively with the flow calculations.
[ top ]
[ top ]
6. TYPICAL RUNNING TIME
The running time of the test case is approximately 170 seconds on the CDC6600. NESC executed the sample problem in 55 CPU seconds on a CDC CYBER175.
The running time of the test case is approximately 170 seconds on the CDC6600. NESC executed the sample problem in 55 CPU seconds on a CDC CYBER175.
NESC1023/01
NEA-DB executed the test case included in this package on a CDC CYBER 740 computer in 589 seconds of CPU time.[ top ]
[ top ]
[ top ]
10. REFERENCES
- Frances Bauer, Paul Garabedian, David Korn, and Antony Jameson,
Supercritical Wing Sections II, Lecture Notes in Economics and
Mathematical Systems, Vol. 108,
M. Beckmann and H. Kuenzi, Springer-Verlag, 1975.
- Frances Bauer, Paul Garabedian, David Korn, and Antony Jameson,
Supercritical Wing Sections II, Lecture Notes in Economics and
Mathematical Systems, Vol. 108,
M. Beckmann and H. Kuenzi, Springer-Verlag, 1975.
NESC1023/01, included references:
- P. Johnson:PROGRAM H Tape Description.
NESC Note 83-70 (March 15, 1983)
[ top ]
NESC1023/01
To run the test case of this package on a CDC CYBER 740 computer, 111,500 (octal) words of main storage are required.[ top ]
NESC1023/01
NOS 1.4-531 (CDC CYBER 740).[ top ]
[ top ]
[ top ]
NESC1023/01
| File name | File description | Records |
|---|---|---|
| NESC1023_01.001 | Information file | 109 |
| NESC1023_01.002 | JCL | 10 |
| NESC1023_01.003 | PROGRAM-H source | 2566 |
| NESC1023_01.004 | Tape 3 sample problem input | 78 |
| NESC1023_01.005 | Tape 4 sample problem input | 52 |
| NESC1023_01.006 | Tape 5 sample problem input | 7 |
| NESC1023_01.007 | Sample problem output | 820 |
Keywords: Fourier transformation, compressible flow, turbulent flow.