- Category:
- Algorithm
- Tags:
-
- File Size:
- 7kb
- Update:
- 2014-04-09
- Downloads:
- 0 Times
- Uploaded by:
- 王逗
Description: This a Fortran source code for solving the flow field around the NACA0012 airfoil at different Mach numbers and angles of attack. The scheme of AUSM, AUSMDV and AUSM+ are employed for this code. In order to improve the calculation accuracy, the MUSCL interpolation with various type limiter are used.
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