engleski

Analisys of Potential Flow Around Wing-Body Configurations

The panel method for the analysis of potential flow around wing-body configuration is applied. The actual geometry is replaced by distributions of singularities, which satisfy the Prandtl-Glauert equation. The restriction of small perturbation compressible flow implies that the panel method applies to configurations with slender bodies and thin wings at low angles of attack. The wing inci-dence is represented by vortex distributions corresponding to pressure differences across the wing. The wing thickness effect is given by source and sinks located over the wing reference plane. The body thickness and incidence are simulated by line sources and doublets placed along the body reference axis. Finally, the interference effects of the wing on the body are cancelled by a vortex distribution on the body surface. Two cases were studied: body-wing configuration and body-wing-canard configuration. The ob-tained results are compared to the experimental data and to the results from the methods of project aerodynamics. It was concluded that the obtained results were in better agreement with experimen-tal data than the project aerodynamics results in the case of the non-standard (body-wing-canard) configuration, where the application of more sophisticated method is required.

Potential Flow; Panel Method; Missile and Aircraft Aerodynamics

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