Application of hypersonic computational fluid dynamics models to low velocity vehicles is examined. The important aspects of the models that were discovered as well as the limits of their applicability are discussed. Modelling aspects such as chemical kinetics, electronic excitation/de-excitation mechanisms, and existence of equilibrium versus non-equilibrium conditions in the flow were examined. Flowfield properties and in-band radiances in the wavelength region of.25μ. in the vicinity of the stagnation streamline are given for a three inch hemisphere. Comparison with recent shock tube data is also shown.
|Original language||English (US)|
|State||Published - Jan 1 1990|
|Event||28th Aerospace Sciences Meeting, 1990 - Reno, United States|
Duration: Jan 8 1990 → Jan 11 1990
|Other||28th Aerospace Sciences Meeting, 1990|
|Period||1/8/90 → 1/11/90|