Effect of Configuration Modifications on the Low-Subsonic Aerodynamic Characteristics of a Space Shuttle Orbiter Concept with a Blended delta Wing-Body

摘要

An investigation of several configuration modifications to improve the subsonic stability and performance of a blended delta wing-body space shuttle-orbiter concept has been conducted in the Langley low-turbulence pressure tunnel. These modifications included variations in vertical- tail location and orientation, wing planform shape, and afterbody shape. The model was tested at a Reynolds number, based on body length, of 17 x one million, at a Mack number of 0.25, and at angles of attack from about - 4 deg to 22 deg. (Author)