The aerodynamic shape of the hypersonic forebody/inlet integrated vehicle is usually designed according to the inviscid flow. However, due to the effect of air viscosity, there is a boundary layer flow near the wall surface. In order to get the actual flow characteristics and performance parameters of the inviscid design vehicle close to the inviscid design values, the inviscid design surface must be corrected by considering the viscous boundary layer. In this paper, the theory and method of the boundary-layer viscous correction (BLVC) for the forebody/inlet integrated configuration are studied. Firstly, two modification schemes of the BLVC for the forebody/inlet integrated configuration are proposed. The calculation method of boundary-layer displacement thickness (BLDT) based on the momentum integral equation of steady two-dimensional (2D) axisymmetric compressible flow is described in detail, and two calculation methods of the BLDT are compared and analyzed. Secondly, the numerical simulation method used in this paper and its validation are introduced. Thirdly, an axisymmetric configuration of the forebody/inlet integration is selected as the first case, and two modification schemes of BLVC are studied and analyzed by numerical simulation. The effects of the two modification schemes of BLVC on the internal and external flow characteristics and aerodynamic performance of the axisymmetric configuration of the forebody/inlet integration are compared and analyzed. Finally, a full-waverider configuration of the forebody/inlet integration is selected as the second case, and the second modification scheme of the BLVC is used to modify the full-waverider configuration. The shock wave characteristics and inlet performance parameters of the modified full-waverider configuration are studied by both the numerical simulation and the wind tunnel experiment. The obtained results prove that the calculation method of the BLDT by a numerical integration method to solve the momentum integral equation of the steady 2D axisymmetric compressible flow is correct and the BLVC method and scheme for the forebody/inlet integrated configuration are effective. The modification scheme 1 of the BLVC can only improve the characteristics of forebody shock wave incident on the inlet lip under viscous conditions, that is, to improve the performance of inlet to capture precompressed air flow, while the modification scheme 2 of the BLVC can simultaneously improve the characteristics of forebody shock wave incident on the inlet lip and the characteristics of the lip shock wave cancelled on the shoulder of the inlet under viscous conditions, and make the air flow capture performance of the inlet and the pressure rise ratio at the inlet exit close to those of the inviscid design state.

高超声速前体/进气道一体化飞行器的气动外形通常是根据无粘流设计的。但由于空气粘度的影响，在壁面附近存在边界层流动。为了使无粘性设计车辆的实际流动特性和性能参数接近无粘性设计值，必须考虑粘性边界层对无粘性设计面进行修正。本文研究了前体/进气道一体化配置的边界层粘性校正（BLVC）的理论和方法。首先，提出了前体/进气口一体化配置的BLVC的两种修改方案。详细阐述了基于稳态二维(2D)轴对称可压缩流动量积分方程的边界层位移厚度(BLDT)计算方法，并比较分析了两种BLDT计算方法。其次，介绍了本文采用的数值模拟方法及其验证。第三，选择前体/进气道一体化轴对称配置作为第一种情况，通过数值模拟研究和分析BLVC的两种修改方案。对比分析了BLVC的两种改型方案对前体/进气道一体化轴对称构型的内外流动特性和气动性能的影响。最后，选择前体/进气道一体化的全乘波器配置作为第二种情况，使用BLVC的第二种修改方案来修改全乘波器配置。通过数值模拟和风洞实验研究了改进的全乘波器配置的激波特性和入口性能参数。得到的结果证明了采用数值积分法求解稳态二维轴对称可压缩流动量积分方程的BLDT计算方法是正确的，前体/进气道一体化构型的BLVC方法和方案是有效的。BLVC 的改造方案 1 只能改善粘性条件下前体冲击波入射到进口唇缘的特性，即：