酸化剤流旋回型ハイブリッドロケットエンジンのC*効率の評価方法について

概要

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The characteristic velocity C* is derived from the assumption of one-dimensional flow in a uniform pressure field, and is usually evaluated using a combustion chamber pressure measured on the chamber wall. In the swirling-oxidizer-flow-type hybrid rocket engines, the C* efficiency in excess of 1.0 was sometimes measured due to an increased wall pressure in the centrifugal force field of the swirling flow. It was induced that the specific impulse efficiency was useful to evaluate the C* efficiency accurately without using the combustion chamber pressure when the CF efficiency was given. This evaluation method of the C* efficiency was confirmed to be appropriate and available by the burning tests using the swirling-oxidizer-flow-type hybrid rocket engines with optimum expanding nozzles.