关键词: 非均匀来流, 三维曲面激波, 微元密切轴对称方法, 乘波体, 高超声速进气道

Abstract: The traditional osculating axisymmetric flow theory is widely used in the inverse design of generalized shock waves under the condition of uniform incoming flows. To solve the inverse problem of the three-dimensional generalized shock wave design under nonuniform incoming flows, a novel method, Micro Osculating Axisymmetric flow (MOA) method, is proposed in this paper. The method constructs a series of micro osculating planes along the shock wave surface in both spanwise and streamwise directions. Actual three-dimensional flows are then approximated by two-dimensional axisymmetric flows in each micro osculating plane. Thus, the new method breaks the restriction of no lateral velocities or lateral pressure gradients in the traditional method. To validate its correctness and feasibility, an internal conical shock wave at a 4° angle of attack, and the other one in an external conical flow of a 10° cone half-angle are reconstructed by the novel method. The CFD results of the two cases indicate that the three-dimensional shock wave geometries completely match the prescribed ones, thereby realizing the control of the three-dimensional shock wave geometry under nonuniform incoming flows. The MOA method has significant application prospects in the field of air-breathing hypersonic forebody/inlet integrated design.

Key words: nonuniform incoming flows, three-dimensional curved shock waves, micro osculating axisymmetric flow method, waverider, hypersonic inlets