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- W2032536782 abstract "This paper is Part I of a comprehensive study on the blade leading edge sweep/bend of supersonic and transonic axial compressors. The objective of the paper is to develop an analytical shock surface model which links a blade leading edge with the 3-D shock structure, and can be eventually explored as a means to estimate the direct and indirect shock losses. The model surface is composed of helixes on a set of cylinders with aerodynamically determined ascendent for each helix. One kind of the relation between the ascendent and 2-D aerodynamics on S1 stream surface has been established for a leading edge attached shock surface. The succeeding research has revealed that the concepts of a forward/backward swept shock surface, and their qualitative and quantitative natures, can be analysed by the model in uniformity. The model is constructed as such that it can also be used in the inverse method of design process. Two leading edge shock surfaces from two high loading transonic fans are simulated by the model." @default.
- W2032536782 created "2016-06-24" @default.
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- W2032536782 date "1999-06-07" @default.
- W2032536782 modified "2023-09-25" @default.
- W2032536782 title "A Helical Surface Model for 3-D Shock Structure Analysis" @default.
- W2032536782 doi "https://doi.org/10.1115/99-gt-226" @default.
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