Analysis of compressible potential flow over airfoils using the dual reciprocity method

Abstract

The use of the linearized potential model for the analysis of compressible flows is quite widespread, and provides good results for subsonic and supersonic flows. However, the calculation of airfoils and wings subject to transonic flows requires a non-linear model, such as the transonic small-disturbance (TSD) potential equation. The solution of the problem by a singularity distribution requires singularities over the field, as well as panels on the boundary, characterizing the procedure known as field panel method. The present work shows results of calculations of the transonic small-disturbance potential equation, with the use of the dual reciprocity method (DRM), which permits calculation of integrals only at the boundary of the problem, without the need of field distributions. This approach, compared to the field panel methods, takes considerably less computer time, which makes this technique adequate to design phases of aircraft. The results show very good agreement with other methods found in literature.