| 摘要 |
<p>The present invention provides a method for controlling an apparatus for sizing an inlet and analyzing its performance in the supersonic aircraft. The apparatus includes an inlet sizing module configured to calculate and output an inlet captured area and a throat area using the inlet design standard of the supersonic aircraft; and a detailed performance analysis module operated in connection with the inlet sizing module, and configured to calculate and output inlet performance using detailed inlet data given to an input file. The present invention as described above calculates inlet sizing using the inlet design standard of the supersonic aircraft, calculates inlet performance using detailed inlet data given to an input file, and performs a performance analysis based on the calculated inlet sizing and inlet performance, thereby easily performing a function of sizing an inlet including an oblique shock inlet in the supersonic aircraft and a performance analysis of its conventional shape. As a result, various performance analyses of the inlet of the supersonic aircraft may be performed.</p> |
