The theoretical potential flow results of Part I are compared with the large number of NACA 65-series compressor blade data. It is found that a single empirical constant used to modify the theory permits reasonable predictions of turning or lift coefficient to be made for any cascade geometry in the unstalled regions of flow. Furthermore, it is demonstrated that the theory allows a considerable number of plus and minus stalling angle of attack data to be collapsed to a single empirical curve. Conversely such a curve, once established, allows stalling predictions to be made for any cascade geometry. One interesting point on this curve is the loading limit above which the cascade is always stalled.

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