| The aerodynamics inverse design problem has been a classic research hot spot for a long time. Numerous research works used to focus on the inverse design based on the given pressure (or velocity) distribution, such as airfoil, nozzle, cascade flow path and inlet, etc. Few work has been done for the inverse design based on the given upstream and outflow profile. The only reference material came from Mark Joel Lewis. He used the compound compressible flow theory to accomplish the modification of supersonic velocity profile. However, the reference voluntarily admits the limitations of the compound compressible flow theory. The basic hypotheses of the compound compressible flow theory are not valid at every circumstance. Studying this problem will inspire the internal flow path design such as2D hypersonic inlet and the basic flowfield of the inward turning inlet, etc.The classic theory of rotational characteristics is used to inverse design the two‐dimension supersonic internal flow path according to the given outflow velocity profile. The design method of curved shock wave is investigated and the corresponding wall shape is obtained by stream trace technology. The basic idea and procedure of “flow field assembling” is demonstrated. Inverse design of velocity profile modification in supersonic flow path using only one shock wave has been achieved. The design models by method of characteristics are all verified by computational simulation. An experimental model is designed based on one of the inverse design example. The parameter profile of outflow obtained in the experiment meet the desire of the inverse design.The inverse design method studied in this paper was used in the design of the basic flow for inward turning inlet. An inward turning inlet is designed accordingly. The inviscid computational simulation showed uniform outflow, while the viscid circumstance had some significant difference. This phenomenon is analyzed with the concept of limiting streamline. |
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