Use of Panel Method in High Subsonic and
Transonic Aerodynamic Analysis of Complex
Aircraft Configuration
Panel Method
Numerical aerodynamic analysis
Computational fluid dynamic
Forward Swept Wing
Aerodynamic Characteristics
Wing-Canard Configuration.
The application of low order panel method with the Dirichlet boundary condition on complex aircraft configuration have been studied in high subsonic and transonic speeds. Low order panel method has been used to solve the case of the steady, inviscid and compressible flow on a forward swept wing – canard configuration with cylindrical fuselage and a vertical stabilizer with symmetrical cross section. The aerodynamic coefficients for the forward swept wing aircraft were calculated using measured wake shape from an experimental work on same model configuration. The study showed that the application of low order panel method can be used with acceptable results
