Abstract
The paper presents the development of a shock-fitting field-panel method for three-dimension (3D) transonic flows. In this method, the full-potential equation, written in the form of the Poisson's equation, is solved by integral equation field-panel method. The solution consists of a wing surface source panel integral term, a field-volume panel integral term of compressibility over a small limited domain, and a shock panel integral term. Due to the non-linearity of flows, solutions are obtained through an iterative procedure. Instead of using a field-panel refinement procedure, a shock-fitting technique is used to fit the shock. Finally, numerical examples are provided to demonstrate the accuracy of the method.
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Communicated by H. Antes and T. A. Cruse, 20 July 1994
This work is supported by NASA-Langley Research Center under the Grant No. NAG-1-1170. Dr. E. Yates, Jr. and Mr. W. Silva were the technical monitors
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Hu, H. Development of a shock-fitting field-panel method for 3D transonic flows. Computational Mechanics 15, 364–371 (1995). https://doi.org/10.1007/BF00372274
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DOI: https://doi.org/10.1007/BF00372274