Top-mounted inlet design and its aerodynamic performance

In the full paper, we explain in detail the results of our UAV (Unmanned Air Vehicle) work. In this abstract, we just list the three topics of explanation and add some pertinent remarks. The first topic is: the design of the top mounted inlet. In this topic, we explain in general terms how to consider various factors in our design. The second topic is: experimental setup. The third topic is: experimental results and their analysis. Its five subtopics are; the measurement of the boundary layer of fuselage (subtopic 3.1), the aerodynamic performance of inlet for different heights of diverter (subtopic 3.2), the flow characteristics of the inlet (subtopic 3.3), the characteristics of the attack angle and the sideslip of the inlet (subtopic 3.4) and the comparison of the aerodynamic performance of the inlet with and without fuselage before it (subtopic 3.5). In all five subtopics, there are figures or tables in the full paper summarizing the experimental results. In subtopic 3.2, we point out that the ratio of the height of diverter to the length of the fuselage before the inlet should be selected as 0.19. The experimental results in topic 3 show preliminarily that the total pressure recovery coefficient of our design reaches a value of between 98% and 99%, better than what was stipulated in design requirements. They also show preliminarily that the variation of inlet pressure distortion index under various conditions is within permissible limits.