Abstract:
This research a low order surface singularity distribution method (panel method) was used to analysis of L39 Aircraft Wing .A computer program was built to predict the influence coefficient matrices by assuming constant source and doublet distribution and applying the Dirichlet boundary condition. The value of the constant source was assumed and, with the influence matrices, the value of the constant doublet was predicted on each panel and wake.
Tangential velocities were calculated giving the value of the pressure distribution. The required lift, drag &moment were then determined.
The results were compared with the obtained computational results. This study give good results which was agreement with the standard figures in modern additional references.
