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, which are potential shocklayer radiators in the midwave 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/set. A detailed vibrational statespecific 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||33rd Thermophysics Conference, 1999 - Norfolk, United States|
Duration: Jun 28 1999 → Jul 1 1999
|Other||33rd Thermophysics Conference, 1999|
|Period||6/28/99 → 7/1/99|
Bibliographical noteFunding Information:
The work at George Washington University was supported by the Army Research Office Grant DAAG55-98-1-009 and at University of Minnesota by the Army Research Office Grant DA/DAAG55-97-l-0406. Computer time was provided by the University of Minnesota Supercomputer Institute. This work is also sponsored in part by the Army High Performance Computing Research Center under the auspices of the Department of the Army, Army Research Laboratory cooperative aggreement number DAAH04-95-2-0003/ contract number DAAH04-95-COOO8, the content of which does not necessarily reflect the position or policy of the government, and no official endorsement should be inferred.