Supersonic Aerodynamic Characteristics of a Lifting-Body Orbiter Model with a Blunted delta Planform at Mach 2.30 to 4.60

摘要

An investigation has been made in the Langley Unitary Plan wind tunnel to determine the aerodynamic characteristics of a lifting-body orbiter model with a blunted delta planform. The model was tested at Mach numbers from 2.30 to 4.60, at nominal angles of attack from -4 deg to 60 deg and angles of sideslip from -4 deg to 10 deg, and at a Reynolds number of 2.5 million per foot. (Author)