Abstract
This paper performs a numerical analysis of the throughflow on a 4 stage compressor as a two-dimensional axisymmetrical flow. The treated case is a flow in the low-pressure compressor of core-engine of former NAL's conceptual Jet VTOL aircraft. This analysis regards the flow field as axisymmetric flow and employ two-dimensional conservation Euler's equation expressed as general coordinates. The case of design point calculation is performed to obtain the acceptable blade designs for the compressor.
