RADIATIVE EFFECTS ON ROCKET STABILITY WITH OZONE-CONTAINING OXIDIZERS.
Quarterly rept. no. 2, 30 Nov 66-28 Feb 67,
DEFENSE RESEARCH CORP SANTA BARBARA CA
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A blackbody radiation spectrum of 4000 K is used to examine the explosion and decomposition flame characteristics of gaseous ozone. Radiation, while not affecting appreciably the flame velocity, alters the flame structure and cuts down the induction period for explosion. The often-invoked assumption that the 0 atom concentration can be approximated by steady-state values for flame calculations is shown to lead to errors. For a given case the computed burning velocity is 70 higher than the values obtained without use of this steady state assumption. From the present analysis it is clear that if the ozone-containing oxidizer is to be used in a rocket at least the two following conditions must be satisfied the injector orifice must be smaller than the quenching distance of the system, and the cooling rate of the injector must be made to balance the heat transfer rate from the decomposition flame to the injector. Author
- Combustion and Ignition