COMPUTATION OF TRANSONIC-FLOWS AROUND A W ING-PLUS-FUSELAGE CONFIGURATION TAKING VISCOUS EFFECTS AND A THIN SEPARATED REGION INTO ACCOUNT

An algorithm and a program were developed for computing the transonic flow around a wing-plus-fuselage configuration taking viscous effects into account. They are based on a semi-inverse viscous-inviscid coupli ng method that also takes the possible existence of a thin separated r egion into account. The inviscid fluid flow is computed by numerically integrating the complete potential equation expressed in conservative form. Two finite difference methods are described for computing the l aminar or turbulent compressible 3D boundary layer. One uses a predict or-corrector scheme and the other an implicit scheme in the transverse plane. These methods are operative in both direct and inverse mode. T he fuselage boundary layer is not taken into account in the applicatio ns processed. However, the results agree well with experimental data.