A computational method which simulates transonic flow about wing-fuselage configurations has been extended to include the treatment of multiple body and non-planar wing surfaces. The finite difference relaxation scheme is characterized by a modified small disturbance flow equation and multiple embedded grid system. Wing-body combinations with as many as four nacelles/pods, four pylons, and wing-tip-mounted winglets can be analyzed. A scheme for modeling inlet spillage and engine exhaust interference effects has been included. Computed results are correlated with experimental data for three transport configurations.
Simulated transonic flows for aircraft with nacelles, pylons, and winglets
Aerospace Sciences Meeting ; 1980 ; Pasadena, CA
1980-01-01
Conference paper
No indication
English
WORLD NEWS ROUNDUP - Suppliers picked for 7E7 pylons, nacelles, reversers
Online Contents | 2004