As a result of some simple experiments on the characteristics of jet-reaction rotor blades, the author found the existence of the pitch angle which makes hovering thrust of rotor maximum regardless of the thrust of tip jet. By some analyses, he then confirmed its existence, and investigated how the lift slope and drag coefficient of wing section affect the value of optimum pitch angle. Comparing the results of analysis with those of experiment, there found some discrepancies, on which the ambiguous characteristics of the blade-root portion seem to have a great influence, and further investigations, especially the Practical method to estimate the effects of this blade-root portion on rotor thrust and torque must be studied.

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