Experimental Study on Aerodynamic Characteristics of Blended-Wing-Body by a Wake Integration Method

摘要

In the present study, a BWB model that has a large sweepback, wash out, and a reflex wing configuration is designed. And, the aims are to obtain basic data of the aerodynamic characteristic of the BWB in low speed flows using the wake measurement. The wind tunnel in this study is a Gottingen type low-speed wind tunnel. The wind tunnel is a return type with an open test section. The shape of the nozzle exit is an octagon having an inner diameter of 1.0 m. The wake survey system has a five-hole probe to obtain static pressures and a stagnation pressure in the wake survey region. The five-hole probe tube is conically-shaped, and made from stainless steel. The inner diameters of each hole are 0.2 mm, and the total diameter is 3.16 mm. The free-stream velocity is kept to be 25 m/s, and the Reynolds number based on the mean aerodynamic chord length is 2.6 × 10~5, respectively. The results are as follows. The section lift coefficient has been generated not only at the wings but also at the center body because the center body was constructed by wing shape. On the section induced drag coefficient, two peaks are seen at the angle of attack 8° and 10°. It seems that the locations of the peaks are at the same locations of the large total pressure loss in the angle of attack 10°. A basic aerodynamic characteristic of BWB was clarified by the present study.