RESULTS OF PHASE CHARGE PAINT TESTS OF O.O40 SCALE 50% FOREBODY MODELS (82-0) OF THE SPACE SHUTTLE ORBITER IN THE AEDC VKF B HYPERSONIC WIND TUNNEL (OH75)

摘要

This report presents po3t-test Information and data from phase change paint, aerodynamic heating wind tunnel tests of a Rockwell International Space Shuttle Orbiter forebody model. These tests were conducted in the Arnold Engineering and Development Center von Karman Facility Tunnel B Hypersonic Wind Tunnel.nThe purpose of these tests was to determine the effect of simulated orbiter protuberances and penetrations (including RCS nozzles) on aero?dynamic heating rates during simulated entry conditions.