Volume 31 Issue 12
Dec.  2016
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ZHAO Qing-wei, PAN Ruo-chi. A method of optimal design of highly-loaded airfoil[J]. Journal of Aerospace Power, 2016, 31(12): 3017-3025. doi: 10.13224/j.cnki.jasp.2016.12.026
Citation: ZHAO Qing-wei, PAN Ruo-chi. A method of optimal design of highly-loaded airfoil[J]. Journal of Aerospace Power, 2016, 31(12): 3017-3025. doi: 10.13224/j.cnki.jasp.2016.12.026

A method of optimal design of highly-loaded airfoil

doi: 10.13224/j.cnki.jasp.2016.12.026
  • Received Date: 2016-07-02
  • Publish Date: 2016-12-28
  • 3-section of cubic Bezier spline was used to fit the tangent of camber line and 2-section of cubic Bezier spline was used to fit the thickness distribution. The airfoil was built on streamline-surface. S1 flow field was evaluated by MISES software and optimization algorithm was performed by genetic algorithm(GA). By introducing a parallel mode to the traditional GA, computational efficiency was improved considerably. Automatic design and optimization of highly-loaded airfoil was achieved and the design criteria of highly-loaded airfoil for design of supersonic airfoil were investigated. Results show that compared with the original airfoil, incident angle range of airfoil I is broadened about 2 degree under the premise that loss coefficient of total pressure reduces a little and the airflow angle of outlet is unchanged; if loss coefficient of total pressure of airfoil II obviously reduces, incident angle range is broadened about 0.6 degree and deviation angle reduces about 3.9 degree.

     

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