This paper presents some practical methods for the aerodynamic design and evaluation of conventional aircraft. High-lift methodology which provides improved takeoff and landing and transonic maneuvering perfqrmance is discussed. A~so, new techni~ues for estimating and minimizing cruise pressure drag are presented. These include a farfield theory to minimize trimmed induced drag, theories to estimate the spanwise variation of drag due to thickness and lift, and a far-field theory to estimate total pressure drag.In addition to the description of methods, aerodynamic design procedures are outlined and results from both the design and evaluation methods are presented. SymbolsAR aspect ratio, b 2 ;S b span CD drag coefficient C Di induced-drag coefficient based on far-field solution c induced-drag coefficient based on near-field solution zero lift drag coefficient for uncanbered configuration lift coefficient design lift coefficient, ~ift coefficient where 100 percent suction polar tangent to locus of optimums (see Fig. 12) optimum lift coefficient, lift coefficient where zero percent suction polar tangent to 100 percent suction polar (see Fig. 12) pitching-moment coefficient normal-force coefficient momentum coefficient, chord Thrust ClooS section drag coefficient section lift coefficient section design lift coefficient section optimum lift coefficient section pitching-moment coefficient section normal-force coefficient *Member AIAA.
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