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The aerodynamic configuration study of ATLLAS-M6 transport aircraft proposed by the German Aerospace Center (DLR) is presented and discussed. The ATLLAS-M6 has a turbine-based combined cycle (TBCC) propulsion system, and it's aerodynamic configuration has the following characteristics, double delta-wing with low-aspect ratio, axial vertical tail, high-set horizontal tail and lifting body with high-fineness ratio. In this paper, a parameterized configuration is proposed via the "class function and shape function transformation technique" (CST) method. The aerodynamic characteristics are investigated, such as the trim characteristic, static/dynamic stability and control efficiency of control surfaces. The detail research indicated that the ATLLAS-M6 analog has a high hypersonic lift to drag ratio at the cruise state of low trimming angle of attack. The hypersonic stability derivatives predicted by the "dahlem-buck" method and the "prandtl-meyer" method shown that the transporter is static and dynamic stable in both lateral and directional directions and the proposed configuration is one of the feasible transporter choices. Yet, the aerodynamic configuration conceptual design of the hypersonic transport aircraft is a highly integrated project, several disciplines involved must be considered farther, such as structured materials and thermal protection system. Therefore, the "multidisciplinary design optimization" (MDO) method would be used to optimize the ATL LAS-M6 analog aerodynamic configuration at the farther work. [ABSTRACT FROM AUTHOR]