This paper develops and explores a new method to analytically generate the compressor characteristic map of an N-stage axial compressor. The accuracy of this new approach is compared to full-blown CFD computations. Based on an initial investigation, the results are in strong agreement for a prototypical 2.5-stage axial compressor. Using this CFD model, the limits of this approximation method is evaluated. This new approach will be valuable to the design community due to its high computational efficiency compared with typical CFD analyses.
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