乘波前体/内转式进气道的一体化构型因同时具有良好的高速升阻特性、较好的来流捕获能力和较高的压缩效率，是未来远程高超声速巡航飞行器的主流选择之一。为了提升一体化构型的设计性能，本文分别从基准流场设计改进和考虑粘性效应两个方面出发，提出了一种定流场分布下考虑粘性效应的乘波前体/内转式进气道一体化设计方法。基准流场设计改进方面，本文将直接控制总压恢复的反射激波波后总压分布改进为二次分布，该分布可通过减小总压变化率来提高总压恢复系数。同时给定利于提高总压恢复的上壁面马赫数反正切分布和中心体壁面流动角贝塞尔分布，反设计了全流道流场分布可控的高总压恢复内压缩基准流场。相较于仅给定上壁面马赫数分布的局部反设计基准流场，其中心体变为渐缩型面，反射激波强度大幅降低，总压恢复系数高达0.98以上。由此生成的一体化构型保持了基准流场的特性，较于定局部流场分布的构型，其内收缩段反射激波和隔离段激波串强度更低，出口流向低能区的占比减小，进而使得设计点升阻比提高15.16%、出口总压恢复提高3.33%、出口畸变降低4.62%。考虑粘性效应方面，本文将高置信度数值求解结果和轴对称边界层位移厚度计算公式结合进行粘性修正，相较于传统二维平板边界层粘性修正，轴对称构型验证算例表明本文方法可以提高型面修正精度，大幅降低与无粘设计性能目标的偏差。采用该方法对原始构型进行粘性修正得到修正构型。较于原始构型，修正构型的前体激波和入射激波在下唇口的封闭性提高，内收缩段反射激波和隔离段激波串的强度下降，激波附面层干扰引起的内流道分离区范围缩小，进而使得设计点流量系数提升了3.22%，设计点喉道和出口的总压恢复系数分别提高了2.41%和0.31%，且在升重平衡和宽速域范围内的气动性能也得到明显改善。综上，本文所提乘波前体/内转式进气道一体化设计具有较优的升阻和进气性能，可为远程高超声速巡航飞行器的气动构型设计提供参考。

The integrated configuration of the waverider forebody and inward turning inlet is one of the mainstream choices for the long-range hypersonic cruise vehicle due to its great high-speed lift-drag characteristics, superior inflow capture ability and high compression efficiency. In order to improve the performance of the integrated configuration, this paper proposes an integrated design method based on improving the basic flowfield design and considering the viscous effect. In terms of improving the basic flowfield design, the total pressure distribution of the reflected shock wave is improved to a quadratic distribution which can reduce the gradient of the total pressure distribution. After giving the anti-tangent Mach number distribution on the upper wall and the Bezier flow angle distri-bution on the center body wall, the high-total-pressure-recovery internal compression basic flowfield with the controllable flow field distribution in the whole flow channel is designed. Compared with the local inverse design basic flowfield with only a given Mach number distribution on the upper wall, the central body of the new basic flowfield becomes a tapered surface, the intensity of the reflected shock wave is greatly reduced, and the total pressure recovery coefficient is greater than 0.98. The resulting integrated con-figuration maintains the characteristics of the basic flowfield. Compared with the configuration with the given local flow field distri-bution, the configuration with the flow field distribution in the whole flow channel is with the lower strength of the reflected shock wave in the inner contraction section and the shock wave train in the isolation section, and the smaller proportion of the low energy region at the exit, which makes the lift-to-drag ratio at the design point increase by 15.16 %, the total pressure recovery coefficient at exit increase by 3.33 %, and the distortion at exit decrease by 4.62 %. In terms of the consideration of the viscous effect, this paper combines the high-fidelity numerical solution results with the displacement thickness calculation formula of the axisymmetric bound-ary layer to carry out the viscosity correction. Compared with the traditional two-dimensional plate boundary layer viscosity correc-tion method, the axisymmetric configuration verification example shows that the proposed method can improve the profile correction accuracy and reduce the deviation from the inviscid design performance target. This method is applied to the viscosity correction of the original configuration to obtain a modified configuration. Compared with the original configuration, the closure of the forebody shock wave and the incident shock wave at the lower lip of the modified configuration is improved, the strength of the reflected shock wave in the internal contraction section and the shock wave train in the isolation section is decreased, and the separation area of the internal flow channel caused by the boundary layer interference of the shock wave is reduced. The flow coefficient at the de-sign point is increased by 3.22 %, and the total pressure recovery coefficients of the throat and exit at the design point are increased by 2.41 % and 0.31 %, respectively. Moreover, the aerodynamic performances at the lift-weight balance point and in the wide-speed range are also significantly improved. In summary, the integrated design of waverider forebody / inward turning inlet proposed in this paper is with better lift-drag and flow-capture performance, which can provide a reference for the aerodynamic design of the long-range hypersonic cruise vehicle.