每年出版 6 期
ISSN 打印: 1948-2590
ISSN 在线: 1948-2604
EXPERIMENTAL INVESTIGATION OF BOUNDARY LAYER STATE ON THE MODEL OF INTEGRATED DESIGN HIGH-SPEED VEHICLE AND ITS IMPACT UPON THE CONVERGENT INTAKE STARTING
摘要
This paper presents the results of an experimental investigation in the TsAGI T-116 wind tunnel to determine the boundary layer state on the windward and compression surfaces of the dorsal intake of an integrated design high-speed vehicle used in the current International "High-Speed Experimental Aircraft" (HEXAFLY-INT) Project. A description is given of the methodology used to carry out the experiments and to process the results in order to establish the wall heat transfer coefficient. Experimental data were compared with numerical results. The boundary layer state on the model surface was determined using a thermal method, particularly on the intake compression surface in the presence of turbulence stimulators, with further consideration of the convergent intake start possibility. In addition to the mass flow rate hysteresis, which accompanies the intake starting, the evidence of boundary layer state hysteresis behavior was found for direct and reverse angle-of-attack changes; these two phenomena do not always occur simultaneously.