Volume 29 Issue 6
Jun.  2014
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QIAO Wen-you, HUANG Guo-ping, XIA Chen, WANG Ming-sheng. Development of inverse characteristic method for matching design of high-speed aircraft forebody/inlet[J]. Journal of Aerospace Power, 2014, (6): 1444-1452. doi: 10.13224/j.cnki.jasp.2014.06.026
Citation: QIAO Wen-you, HUANG Guo-ping, XIA Chen, WANG Ming-sheng. Development of inverse characteristic method for matching design of high-speed aircraft forebody/inlet[J]. Journal of Aerospace Power, 2014, (6): 1444-1452. doi: 10.13224/j.cnki.jasp.2014.06.026

Development of inverse characteristic method for matching design of high-speed aircraft forebody/inlet

doi: 10.13224/j.cnki.jasp.2014.06.026
  • Received Date: 2013-04-02
  • Publish Date: 2014-06-28
  • In order to solve the problems of robustness and accuracy for the given shock's aerodynamic surface, a kind of inverse characteristic method was developed. This method could be used to generate the aerodynamic surface and dependent domain flow field for the given shock wave in a non-uniform upstream. Numerical verification indicated that the relative error of the cone shape (cone angle) gotten by inverse characteristic method was less than 0.5 ‰,when the conical shock was given at Mach number of 5; the calculations of two-stage axisymmetric shock showed that the two-stage compression cone corresponding to the flow field could be accurately acquired. Finally, three aerodynamic models were obtained with use of the method, including: Bump surface with two-stage shock wave and waverider forebody at Mach number of 4 and the integration of the wave precursor and inlet. The CFD calculation results show that these models are better designed and the inverse characteristic method proposed provides a way for aerodynamic design.

     

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