Heat Transfer Measurements on the Afterbody of Spheres in Hypersonic Free-Flight in Air and Carbon Dioxide

摘要: The use of thermal imaging techniques to measure convective heat transfer on the forebody ballistic-range models has previously been demonstrated. Application afterbody poses several challenges. In particular, surface temperatures are relatively low, and hypersonic wake flow is self-luminous generally radiates much more intensely than model surface. Approaches overcome these challenges were explored, heat-transfer measurements obtained base spheres in flight through air CO2 at speeds between 3.33 km/s 5.11 km/s. Over this range conditions, measured flux sphere averaged 5.8% stagnation point flux.