On the Formation of Nitrogen Oxides During the Combustion of ...

B Investigated Conditions
high mechanical loads on the experimental setup, and very high costs. Key
data regarding payload and rocket operation is given in Chapter C.1 for sounding
rocket flights in general and the PHOENIX mission in particular.
Despite the limitations and additional effort, the “Japanese Combustion Module”
(JCM) was retrofit and customized for sounding rocket flight. This was
due to the scientific experiments requiring microgravity in excess of 40s for
every single combustion run. These extended microgravity times alone allowed
for an in-depth investigation of the degree of fuel pre-vaporization in
droplet combustion. The TEXUS sounding rocket system was chosen for this
purpose, and the flight of the associated PHOENIX mission was finally performed
on TEXUS-46 in Kiruna, Sweden, in November 2009.
B.2 Supplementary Data on Numerical Simulations
In order to enforce ignition of partially pre-vaporized droplets, a volumetric
heat source is applied in the gas phase (cf. Figs. 4.2 and 4.3). Figure B.1 shows
the maximum volumetric heat release ˙q v,max of this external heat source. Here,
8 x 10 9
W m −3
Maximum volumetric
heat source qv,max
6 x 10 9
4 x 10 9
2 x 10 9 Dependence of heat source profile on
position of mean radius r m
Maximum volumetric heat source values
employed in numerical simulation runs
0 x 10 9
0.0 x 10 −3 0.2 x 10 −3 0.4 x 10 −3 0.6 x 10 −3 0.8 x 10 −3 1.0 x 10 −3 m
Radial coordinate r
Figure B.1: Maximum Value of Volumetric Heat Source in Relation to its Radial Position.
212