Preliminary weight estimation of conventional and joined wings usingequivalent beam models

Subsonic and supersonic chordwise pressure distribution are shown in Fig. 2. Figure 2a shows a large drop in leading-edge pressures as a result of optimization. Optimization results in evenly distributed chordwise loading and the adverse pressure gradient shifts further rearward, delaying flow separation. The local load distribution toward the wing tips is reduced by optimization, decreasing the root-bending moment. In supersonic flow, some drop in leading-edge pressure is observed as a result of optimization (Fig. 2b); however, peak loading and the start of the adverse pressure gradient remain close to the leading edge. Reduction in local load distribution toward wing tips due to optimization is marginal because of the conical nature of the flow.