1. The Discretization Procedure
2. This test-case examines the nonplanar interference between a rectangular wing and tail (Figure 5). The tail is vertically separated from the wing by 0.4 units. Figures 6-8 show the chordwise pressure distributions at 5%, 45%, and 95% span locations, respectively, when the wing undergoes uniform plunging oscillations at kZ0.2 and M=1.2. Good agreement is observed in these figures with the Mach Box method . Results are obtained with 200 boxes in the DPM and 300 boxes on surfaces (plus additional boxes in the diaphragm region1 in the Mach Box method.
3. o'80 1 -0.40 ' I I I I v I t I I I I I 8 I I I I t I I 0 I
4. Doublet-Point Method 3 1oo:oo 150100 200100