This paper presents a methodology for the calculation of the IR shocklayer radiance from a slender hypersonic vehicle. An overlay technique that has been successfully employed for chemically reacting hypersonic compressed and expanding flows has been extended to accurately model the vibrational state distributions of NO, CO, water and CO2, potential shocklayer radiators in the mid-wave infra-red. The spectral predictions show that radiation from shock heated ambient CO2 will be an important contribution at most altitudes and speeds slower than 3. 5 km/sec. A detailed vibrational state-specific model of CO2 excitation has been incorporated with the flow modeling using an overlay technique. Comparisons of the spatial distributions of CO2 vibrational states with a corresponding Boltzmann distribution at the translational temperature show that there are substantial differences in the populations. These predictions are important for the design of an upcoming sounding rocket experiment.
|Original language||English (US)|
|State||Published - 1998|
|Event||7th Joint Thermophysics and Heat Transfer Conference, AIAA/ASME 1998 - Albuquerque, United States|
Duration: Jun 15 1998 → Jun 18 1998
|Other||7th Joint Thermophysics and Heat Transfer Conference, AIAA/ASME 1998|
|Period||6/15/98 → 6/18/98|
Bibliographical notePublisher Copyright:
© 1998, American Institute of Aeronautics and Astronautics, Inc.