Application of electrooptical pyrometry to re-entry vehicle nose-tip testing in a hyperballistics range

Combined experimental and analytical programs are being conducted in support of current and future strategic re-entry systems. This paper reports on present capabilities for creating free-flight re-entry environments within a 1000-foot hyperballistics range and for accurately measuring surface-temperature contours on models exposed to such environments. Details on an electrooptical-pyrometer system are described, and limiting assumptions in data reduction and interpretation are discussed. Surface-temperature contours measured on an ablating graphite hemisphere are presented, and comparisons made with calculations generated by a currently utilized nose-tip design code.