Abstract: As one of the main configurations of the next generation's commercial aircraft, Blended-Wing-Body (BWB) configuration aircraft has attracted more and more attention. While the research of BWB aircraft is mainly focused on the characteristics of its cruise phase, few have studied the stall characteristics. In this paper, the BWB is studied by wind tunnel test. The configuration of the non-lift device and the longitudinal characteristics of the composite components with winglet, leading edge slat, and double nacelles are studied by the force measurement method, especially the stall characteristics. The flow mechanism of the stall process is studied by the two-dimensional image testing technology. The results show that the BWB aircraft can maintain low-speed flight in the basic configuration without lift-up device, and the combination configuration has the effect of increasing lift coefficient. And with the increase of the angle of attack, the separation region gradually develops from the wing tip to the wing root and the fuselage. When the outer wing is completely in the separation region, the aircraft will not stall immediately. Because the centrosome also provides lift, and the flow separation of the centrosome is later than the outer wing. Therefore, when the outer wing causes lift loss at stall angle of attack, the lift of the centrosome can be compensated to maintain its low-speed flight phase. The real stall occurs after the flow separation of the centrosome.

Key words: blended-wing-body, wind tunnel test, stall characteristics, flow field analysis, force measurement analysis