Abstract
This paper presents the design logic and optimization techniques that resulted in the Shuttle Orbiter aerodynamic configuration. Design requirements which are key configuration drivers are landing speed, payload center of gravity envelope, crossrange requirements, lateral-directional stability and control requirements, and flying qualities. Trade studies based on these requirements, subject to constraints on vehicle weight, establish wing, fuselage, and tail geometry, control surface size and geometry, and local contours and configuration details. Additional studies refine the configuration design in terms of wing aspect ratio, trailing edge sweep, twist, camber, forebody shaping, and vertical tail geometry.
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