Accession Number:

AD0766249

Title:

Transonic Flow Around Compressor Rotor Blade Elements. Volume II. Digital Program User's Manual.

Descriptive Note:

Final rept. 1 Dec 71-30 Jun 73,

Corporate Author:

GENERAL MOTORS CORP INDIANAPOLIS IND DETROIT DIESEL ALLISON DIV

Personal Author(s):

Report Date:

1973-08-01

Pagination or Media Count:

71.0

Abstract:

A computer program to analyze steady-state transonic flow in turbomachinery components has been developed. The time-dependent partial differential system of equations is approximated by the MacCormack finite-difference algorithm. The program is operational for two-dimensional compressor cascades or quasi-three-dimensional rotors including radius and stream surface thickness variations. A hybrid method of characteristics is used to impose the boundary constraints upon the flow field. Flow field periodicity is used at the free surface boundaries. Output consist of a flow field description and mixed-out properties of the flow at the exit. Author

Subject Categories:

  • Computer Programming and Software
  • Fluid Mechanics
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE