Automatic computation of wing-fuselage intersection lines and fillet inserts with fixed-area constraint

Abstract

Procedures for automatic computation of wing-fuselage juncture geometry are described. These procedures begin with a geometry in wavedrag format. First, an intersection line is computed by extrapolating the wing to the fuselage. Then two types of filleting procedures are described, both of which utilize a combination of analytical and numerical techniques appropriate for automatic calculation. An analytical technique for estimating the added volume due to the fillet is derived, and an iterative procedure for revising the fuselage to compensate for this additional volume is given. Sample results are included in graphical form. Introduction Reference 1 describes methods that are often used for a rapid, approximate analysis of initial "rough cut" supersonic aircraft designs. The methods use a geometry input format of the wave-drag type (ref. 1). The fuselage is input in x = Constant sections. For the wing, airfoil sections are input at y = Constant stations in the form of individual camb...