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- Two and three dimensional inviscid solutions for the flow in a transonic axial compressor rotor at design speed are compared with probe and laser anemometers measurements at near-stall and maximum-flow operating points. Experimental details of the laser anemometer system and computational details of the two dimensional axisymmetric code and three dimensional Euler code are described. Comparisons are made between relative Mach number and flow angle contours, shock location, and shock strength. A procedure for using an efficient axisymmetric code to generate downstream pressure input for computationally expensive Euler codes is discussed. A film supplement shows the calculations of the two operating points with the time-marching Euler code.
- Other Subject(s):
- NASA Technical Reports Server (NTRS) Collection.
- Document ID: 19830024503.
Accession ID: 83N32774.
ASME 27th Intern. Gas Turbine Conf.; 18-22 Apr. 1982; London.
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View MARC record | catkey: 15711818