Field panel method with grid stretching technique for solving transonic potential flow around arbitrary airfoils. (English) Zbl 0828.76065
From the authors’ summary: The field panel method with grid stretching technique is developed for solving transonic full potential flow around arbitrary airfoils at incidence. In this method, the potential values are represented by boundary integrals together with a volume integral. The boundary potential values are obtained by implementing a standard panel method (symmetric singularity model), whereas the field potential values are estimated by solving the full potential equation (using AF3 scheme on a Cartesian grid) with approximate inner proper outer boundary conditions. Furthermore, the grid stretching technique has been utilized which allows to capture the shock waves in a much better quality. Results for transonic potential flows about NACA 0012 and RAE 2822 airfoils at different Mach numbers and incidences are obtained and compared with other numerical solutions.
Reviewer: Titus Petrila (Cluj-Napoca)
MSC:
| 76M25 | Other numerical methods (fluid mechanics) (MSC2010) |
| 76H05 | Transonic flows |
Keywords:
symmetric singularity model; boundary integrals; volume integral; boundary potential values; field potential values; shock waves; NACA 0012; RAE 2822References:
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