DCE TEST MATRIX

Droplet Combustion Modeling Results

Prof. Frederick L. Dryer
Dept. of Mechanical and Aerospace Engineering
D-316 Engineering Quadrangle
Princeton University, Princeton, NJ 08544

(609) 258-5206; Fax: (609) 258-1939
e-mail: fldryer@phoenix.princeton.edu

Summary of Calculations

Many of the experimental test points in the overall matrix for the Droplet Combustion Experiment (DCE) have been simulated using a time-dependent, finite element, chemically reacting flow model (Marchese, 1996). The calculations use a recently-developed n-heptane mechanism (Held, et al., 1997) along with detailed molecular transport. The calculations also consider the effect of non-luminous gas phase radiation (Marchese and Dryer, 1997).

The predictions shown here were performed in advance of the flight experiments to assist in the selection of test matrix conditions. The calculated results are presently being further refined in preparation for publication. If the reader is interested in quoting any of the results presented here, please contact Prof. Dryer.

Test Matrix

Bottle No.	Test Point No.	Ox. Environment	Pressure	Diameter
01	D103515A	65% He / 35% O2	1 Atm	1.5 mm
01	D103530A	65% He / 35% O2	1 Atm	3.0 mm
01	D103550A	65% He / 35% O2	1 Atm	5.0 mm
02	D103015A	70% He / 30% O2	1 Atm	1.5 mm
02	D103030A	70% He / 30% O2	1 Atm	3.0 mm
02	D103050A	70% He / 30% O2	1 Atm	5.0 mm
03	D102515A	75% He / 25% O2	1 Atm	1.5 mm
03	D102530A	75% He / 25% O2	1 Atm	3.0 mm
03	D102550A	75% He / 25% O2	1 Atm	5.0 mm
06	D504015A	60% He / 40% O2	0.5 Atm	1.5 mm
06	D504030A	60% He / 40% O2	0.5 Atm	3.0 mm
06	D504050A	60% He / 40% O2	0.5 Atm	5.0 mm
07	D503515A	65% He / 35% O2	0.5 Atm	1.5 mm
07	D503530A	65% He / 35% O2	0.5 Atm	3.0 mm
07	D503550A	65% He / 35% O2	0.5 Atm	5.0 mm

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http://www.princeton.edu/~fldryer/nasa.dir/current3.htm
Last updated: July 3, 1997