DISCHARGE OF CF3I IN A COLD SIMULATED AIRCRAFT ENGINE NACELLE 

Jiann C. Yang§, Samuel L. Manzello, and Marc R. Nyden 

Building and Fire Research Laboratory 

National Institute of Standards and Technology 

100 Bureau Drive, Gaithersburg, Maryland 20899, U.S.A. 

Michael D. Connaghan 

U.S. Army CECOM Research, Development, and Engineering Center 

Fort Belvoir, Virginia 22060, U.S.A. 

§

Telephone: (301) 975-6662 

Fax: (301) 975-4052 

E-mail: jiann.yang@nist.gov, samuel.manzello@nist.gov, marc.nyden@nist.gov, Michael_D_Connaghan@belvoir.army.mil

INTRODUCTION 

An aircraft engine nacelle refers to the region between the engine body and its casing. Fuel and 

hydraulic lines, pumps, and lubrication systems are located within the nacelle. Air is vented 

through the nacelle to prevent any build-up of combustible vapors, and underside drain holes are 

used to mitigate potential pooling of flammable fluids as a result of a leak. Once a fire is 

detected in the nacelle, the pilot will first level the aircraft before arming and discharging the fire 

suppressant. Depending on the configuration of the aircraft, the fire suppression bottle is 

mounted either adjacent to the engine nacelle or at a location several meters away from the 

nacelle, and the agent is transported through piping to the fire zone. 

Current aircraft fire suppression bottles for engine nacelle fire protection are normally filled with 

liquid CF3Br (halon 1301) to about half of the bottle volume, and the bottle is then pressurized with 

nitrogen to a specified equilibrium pressure (typically ≈ 4.1 MPa) at room temperature. The 

purpose of using the pressurization gas is to expedite the discharge of the agent and to facilitate the 

dispersion of the agent. Without nitrogen pressurization, the bottle pressure, which is simply the 

vapor pressure of the agent, can be so low at cold ambience that there is not enough driving force 

to rapidly expel the agent from the bottle when needed. 

Present military specification (MIL-E-22285) [1] for CF3Br in engine nacelle applications calls 

for a discharge time of less than 0.5 s and an amount of agent corresponding to a dwell time of 

0.5 s throughout the protected nacelle space with an agent volume fraction of at least 0.06 at 

normal cruising condition. The certification process for the fire suppression system requires the 

use of a Halonyzer, a Federal Aviation Administration certified instrument, with 12 measurement 

probes positioned throughout the protected space to monitor the temporal CF3Br concentration 

upon the discharge of the agent. 

Due to its adverse effect on the ozone layer, halon 1301 has been banned from production in the 

United States since 1994 in compliance with the Montréal Protocol On Substances That Deplete 

The Ozone Layer. Many studies have since been conducted to identify alternatives to replace 

halon 1301. Trifluoroiodomethane (CF3I) has been proposed as a potential replacement for 
halon 1301 in aircraft engine nacelle fire protection applications [2,3]. One important aspect 

pertinent to CF3I applications in an engine nacelle is the discharge behavior of the agent when it 

is exposed to ambient temperatures well below its normal boiling point. Such a condition may 

be encountered during a cold start of an engine on a cold tarmac or high-altitude cruising. 

Table 1 lists some of the physical properties of CF3I. For comparison and reference, the

properties of CF3Br are also given in the table. Since CF3I has a normal boiling point of −22 oC, 

the dispersion of CF3I into air at temperatures down to −40 °C may not be as effective as halon 

1301, which has a normal boiling point of −57.8 oC. 

Table 1. Selected physical properties of CF3I and CF3Br [4].

Agent Molecular weight

(kg/mol) 

Tb

(oC) 

Tc

(oC) 

Pc

(MPa) 

ρc

(kg/m3) 

Ps @ −40 oC

(kPa) 

∆Hv

(kJ/kg) 

CF3I 0.196 −22.0 122.0 4.04 871 44.77* 106

CF3Br 0.149 −57.8 67.0 4.02 745 224.4§ 111

Tb is the normal boiling point; Tc is the critical temperature; Pc is the critical pressure; ρc is the critical density; Ps is

the vapor pressure, ∆Hv is the latent heat of vaporization at Tb. *

 from [5]

§

 from [6]

The release of CF3I (at room temperature or chilled to about −40 °C) into a fire compartment and 

an engine nacelle simulator at ambient room temperature has been examined [4,7]; however, the 

discharge of cold CF3I into a cold ambience has not been performed, or at least has not been 

documented in open literature. To the best of our knowledge, there is only one corporate internal 

report [8], which describes a study of the release of cold CF3I into a well-mixed cold enclosure

with no airflow. Careful examination of the data indicated some deterioration in the distribution 

of CF3I within the enclosure when compared to room temperature conditions. In order to assure

that there is no substantial deterioration in dispersion performance of CF3I under cold 

temperature applications, discharge tests in an aircraft engine nacelle with airflow at −40 °C are 

needed. The temperature of −40 °C was selected in this study because it was below the normal

boiling point of CF3I and was the lowest operating temperature for some of the equipment used 

in the experiments. 

At the HOTWC 2001 workshop [9], we presented some experimental data based on a series of 

discharge tests using CF3I in a simulated aircraft engine nacelle with CF3I (initially pressurized

with nitrogen to ≈ 4.1 MPa at room temperature) at either –40 oC or room temperature and 

airflow at room temperature. Since then, we have modified the nacelle simulator to better mimic 

the geometry and the flow characteristics inside a real nacelle. Using the modified simulator, we 

have performed CF3I discharge tests at –40  ̊C with airflow through the nacelle at –40 oC. This 

paper reports some of the data obtained from these tests. 

APPARATUS 

The experimental apparatus consisted of a simulated engine nacelle with baffles, an agent release

port, four observation windows, and two measurement ports. Figure 1 is a schematic of the

2
simulator. The annulus of the simulator had an inside diameter of 0.6 m and an outside diameter

of 0.9 m, resulting in a cross-sectional area of 0.35 m

2

. The length (2 m) of the simulator was 

comparable to the distance between the agent injection port and the downstream end of a typical 

small engine nacelle. The baffle height was 0.075 m. The baffles were used to mimic a

complicated flow path for the agent transport as in the case of a real nacelle. To modify the 

existing simulator [9], two baffles were added to the inner surface of the outer cylinder, and two 

longitudinal ribs with the same height as the baffles were placed on the outer surface of the inner 

core of the nacelle between the inner forward and aft baffles (see Figure 1). The ribs were used 

as barriers to prevent the agent from flowing circumferentially. The simulator was fabricated of

3.2 mm thick stainless-steel sheet metal. 

To exhaust

Video camera

Baffle

Air from blower

Observation window

2 m

60 cm

Pitot tube

15 cm

Agent bottle

Fiber-optic probes (UV spectrometer)

Agent release location

Simulated

engine core

1

2

3 4

Horizontal rib

Figure 1. Schematic of the simulated engine nacelle. 

A receiver bottle (Pacific Scientific1

, P/N 36200122) with an internal volume of 2.36 L was used 

to store CF3I for discharge. A fast-response static pressure transducer (uncertainty ± 10 kPa) was 

mounted on the receiver bottle to monitor the pressure inside the bottle during filling and 

discharge. A K-type thermocouple (uncertainty ± 1 °C) was inserted into the bottle to record the 

temperature of the liquid agent before discharge. The agent was released using a quick-acting

solenoid valve (Pacific Scientific, P/N 36400036). To tailor the agent discharge time (< 0.5 s), a 

reducer was placed at the valve exit. The agent was released through a vertical tee at the end of a

short stainless-steel tubing (i.d. = 15.9 mm, o.d. = 19.1 mm) connected to the reducer. 

Four CCD cameras (30 frames/s) were used to observe the agent discharge behavior at the 

release port (Camera 1), at a location in the bottom of the simulator to observe any pooling of 

 1

 Certain commercial products are identified in this paper in order to specify adequately the equipment used. Such 

identification does not imply recommendation by the National Institute of Standards and Technology, nor does it 

imply the equipment is the best available for the purpose.

3
agent (Camera 2), and at the two concentration measurement locations (Cameras 3 and 4), 

respectively. A frequency-controlled, variable-speed blower provided airflow through the 

nacelle simulator. The maximum air speed in the annulus, measured using a pitot tube, can reach

9.2 m/s at room temperature. 

To achieve an operating temperature of –40 °C, the entire facility was housed inside the U.S. 

Army environmental test chamber at Ft. Belvoir, and the cold discharge experiments were

conducted inside the chamber. The chamber has an interior dimension of 2.74 m (H) × 3.35 m 

(W) × 3.66 m (L) and a 1.83 m × 1.83 m sliding door. The lowest temperature attainable in the 

environmental test chamber is −54 °C. Discharge experiments at room temperature were also

conducted inside the chamber without running the refrigeration unit to establish baselines for

comparisons. 

The experimental procedure involved the following steps. The receiver bottle was first filled 

with the required amount of agent and then pressurized with nitrogen to ≈ 4.1 MPa at room 

temperature. The bottle was connected to the discharge plumbing of the simulator and was ready 

for a discharge experiment. For cold temperature conditions, the environmental test chamber and 

the receiver bottle were cooled down to −40 °C before a test was commenced. Two contact Ktype thermocouples were attached on the front and aft of the simulator external skin to monitor 

the ambient temperature of the chamber. In addition, a bare-beaded K-type thermocouple was 

placed in the annulus to measure the air temperature through the nacelle. 

Based on the simulated nacelle volume and airflow, the amount of agent required for a fixed 

injection period (< 0.5 s for typical nacelle applications) was estimated using the generic nacelle

modeling results discussed in Hamins et al. [10]. The agent bottle was charged with ≈ 1 kg of

CF3I and then pressurized with nitrogen to the desired pressure (≈ 4.1 MPa) at room temperature. 

Table 2 lists the experimental matrix. The airflow through the simulator was maintained at 

1.5 kg/s ± 0.1 kg/s (mean ± standard deviation). 

Table 2 Experimental matrix. 

Nominal initial conditions of

vessel 

Nominal conditions of vessel 

before discharge 

Nominal conditions in the 

simulator 

22 oC and 4.12 MPa –40 oC at prevailing P§ –40 oC §

22 oC and 4.12 MPa 22 oC and 4.12 MPa 22 oC (baseline) 

22 oC and 4.12 MPa –40 oC at prevailing P∗ 22 oC 

§ Tests were performed in the environmental test chamber. ∗ Dry ice was used to cool the vessel.

The dispersion effectiveness of CF3I was assessed based upon concentration measurements at the 

two locations inside the engine nacelle simulator (see Figure 1). Note that the intent of this work 

is not to address the certification process, which requires twelve measurement locations. The 

measurements were made using two Ocean Optics S2000 UV/VIS fiber-optic spectrometers. 

The optical components consisted of a deuterium/tungsten source, four (UV grade quartz) 

collimating lenses, and 300 μm diameter optical fibers. These were arranged to provide two 

4
measurement locations (coincident with Cameras 3 and 4) approximately 0.75 m apart along the 

direction of the airflow in the engine nacelle testing apparatus. A bifurcated fiber (1 m in length, 

coupled with a 5 m extension) was used to connect the source to a pair of collimating lenses 

secured by brackets to the Plexiglas viewing windows located on the top of the apparatus. The 

source radiation emanating from each lens was transmitted over a 0.038 m optical path 

(perpendicular to the airflow) to an opposing set of collimating lenses connected by independent

optical fibers (5 m in length) to the master and slave spectrometers. Although the specifications 

indicated that these optical components should have a spectral range from 200 nm to 850 nm,

very little throughput at wavelengths shorter than 250 nm was found. 

The two spectrometers were software triggered by an electronic timer. The integration time 

(analogous to the shutter speed) was set at 30 ms, and the pixel resolution of the analogue to 

digital converter (ADC) was set at 10, which amounts to a spectral resolution of only about 3 

nm. With this configuration, we were able to achieve a data acquisition rate of approximately 12 

single scan spectra (6 at each location) per second to capture the time dependent details of the 

agent discharge. 

An electronic timer was used to coordinate the experimental sequence of events. At t = 0 s, a 

signal was sent from the timer to trigger the data acquisition system to record the pressure of the 

discharge bottle and the pitot tube output at a sampling rate of 200 Hz. At t = 1 s, the timer 

initiated the two UV spectrometers, and at t = 2 s, the solenoid valve was activated to discharge 

the CF3I/nitrogen mixture from the bottle into the engine nacelle simulator.

RESULTS AND DISCUSSION 

The observations from Camera 1 showed that the agent discharge time at –40 oC was longer than 

that at room temperature. When CF3I was discharged at room temperature with airflow at the 

same temperature, the observations obtained from Camera 2 showed that a small amount of CF3I 

pooled in the bottom of the simulator upon release. However, the liquid CF3I boiled off within 

66 ms. On the contrary, when CF3I was discharged at –40 oC with airflow at –40 oC, a 

significant amount of liquid CF3I pooled at the bottom of the nacelle upon release. The liquid 

CF3I evaporated slowly and remained for many seconds (> 60 s) before complete evaporation. 

Intermediate behavior was observed when CF3I was discharged at –40 oC with airflow at room 

temperature. The observations from Cameras 3 and 4 showed that a cloud of CF3I passed

through the field of view of the cameras after agent discharge. The observations from Cameras 3 

and 4 were qualitatively similar for the discharge of CF3I at room temperature and –40 °C,

irrespective of the temperature of the airflow. 

The differences in pooling tendency described above can be explained in part due to the resulting 

high liquid fraction when the agent/nitrogen mixture is released at –40 oC [4]. In addition, if the 

nacelle surface is at –40 oC, the evaporation of the liquid pool will be very slow. The combined 

effects of pooling and slow evaporation will have an adverse impact on the subsequent 

dispersion of the agent/nitrogen mixture in the nacelle at –40 oC. 

The UV spectrometer was calibrated at 295 K using a quartz cell with an optical path length of

0.075 m. The cell was first evacuated to 1.33 Pa. Then, a fixed amount of CF3I vapor was 

5
metered into the cell by monitoring the cell pressure. Spectra were taken using an integration 

time of 30 ms and a pixel resolution of 10. Figure 2 shows a typical CF3I absorption spectrum. 

Note that the peak absorbance for CF3I centers around 270 nm. Although full CF3I spectra were 

obtained in each test, a common practice used in spectroscopy to obtain the concentration

measurements from the spectra is based on the wavelengths at the peak absorbance or its

vicinity. The spectrometer is also equipped to take absorbance measurements at three specified

wavelengths in addition to the full spectra. The wavelengths selected were 280 nm, 300 nm, and 

500 nm. The absorbance at 300 nm was used to obtain the CF3I concentration because saturation 

of the detector in the spectrometer at ≈ 280 nm was observed in some cases. The measurements 

at 500 nm (off-resonance) were used to indicate the presence or absence of liquid CF3I droplets 

in the flow (see discussion below). 

0

0.5

1

1.5

2

250 300 350 400

2.6 kPa CF

3

I

Abs

orbance

Wavelength (nm)

Figure 2. A typical CF3I absorption spectrum. 

The calibration curve (at λ = 300 nm and 295 K), which is a plot of absorbance (A) against 

concentration (C, molecules cm-3), is shown in Figure 3. 

According to the Bouguer-Beer-Lambert law, 

 ( ) ( )

( )

( )

2 303

σ λ,

λ

λ λ log .

C T L

I

I A

o

 =



 



 = − (1) 

6
where I(λ) and Io(λ) are the incident and transmitted intensities through the cell respectively,

σ(λ,Τ) is the absorption cross section (cm2

), L is the optical path length (cm), T is the 

temperature, and λ is the wavelength. Note that the absorption cross section is a function of

wavelength and temperature. Using the ideal gas law, Equation (2) gives the relationship 

between C and the partial pressure p (Pa) at 295 K. 

 C . p (2) 14 = 2 44×10

0

0.2

0.4

0.6

0.8

1

1.2

0 0.5 1 1.5 2 2.5 3 3.5 4

at λ = 300 nm

A

b

s

o

r

b

a

n

c

e

 (molecules / cm

3

) x 10-18 C

Figure 3. Calibration curve. 

From Equation (1), the absorption cross section can be obtained from the slope of the calibration 

curve. A linear regression line is fitted through the data points in Figure 3, and the absorption 

cross section of CF3I is 8.1×10-20

 cm

2

, which is comparable to the value of 8.9×10-20 cm

2

 at λ = 

300 nm and 295 K to 300 K in the literature [11]. Since the calibration was performed at 295 K, 

a correction for the temperature effect on the absorption cross section is necessary to obtain the 

CF3I partial pressure at other prevailing temperatures, using the following equation [11]: 

σ( ) λ ,T = σ(λ ,298 K) exp[B(λ)(T − 298)] 210 K < T < 300 K (3) 

The concentration C of CF3I at any temperature was calculated from the absorbance

measurement using Equations (1) and (3). At 300 nm, B = 4.876×10-3 K-1 [11]. The partial 

pressure of CF3I was then obtained using the ideal gas law at the prevailing temperature.

7
However, the temperature effect on the absorption cross section was found to be negligible in the 

concentration calculations. 

An estimate of the uncertainty (one standard deviation) of our measurements was obtained by 

comparing results at these settings to more accurate values obtained after signal averaging 100 

scans at the full resolution of the spectrometer (≈ 0.3 nm). Based on this analysis, the CF3I 

partial pressures reported in this paper are accurate to ± 15 %. 

The concentration of CF3I obtained at 300 nm is shown for both the room and cold temperature 

releases in Figures 4 and 5 for the two measurement locations, respectively. The initial time (t = 

0) in the figures corresponds to the initiation of the agent release. Although three runs were 

performed at each condition with similar observations, only a single run for each condition is 

shown in the figure for clarity. The arrival times of the agent at the two measurement locations 

were clearly captured in the figures. Some salient features are noted in the two figures. 

0

5

10

15

20

0 5 10 15 20 25 30

Room temperature release, forward port

Room air / Cold agent release, forward port

Cold temperature release, forward port

Volume Fra

ction (%)

Time (s)

Figure 4. Concentration profiles of CF3I at the forward measurement location under three test 

conditions.

For the room temperature release (both agent and air at room temperature), an initial spike was 

observed at the forward measurement location. This was due to the presence of a two-phase 

(liquid droplet-laden) flow because the off-resonance spectral measurement at 500 nm also 

showed a peak at the same time. The two-phase flow was the result of break-up of the liquid

core into droplets at the discharge port. The off-resonance extinction at 500 nm indicated that 

8
liquid CF3I droplets were present for only a short period of time (< 2 s) immediately following 

the discharge. Therefore, it can be argued that the concentration measured after the initial spike

in Figure 4 was due largely to the CF3I vapor with minimal contribution from the droplets. The 

off-resonance spectral measurement at 500 nm in the aft location indicated that no droplets were

present. The absence of the droplets and the much lower CF3I concentration (see Figure 5) at 

this location indicated that the current nacelle simulator had indeed created a very challenging 

environment for agent dispersion, a condition which is generally true for a real engine nacelle. 

Furthermore, the generic nacelle model [10] provided a reasonable estimate of the amount of 

agent needed to achieve the required extinguishing concentration in the current nacelle. Halon 

1301 and CF3I have similar heptane cup-burner extinguishing concentration, a volume fraction 

of 0.032 [2]. Assuming that the military specification for halon 1301 can be applied to CF3I, the

measurements in Figures 4 and 5 suggest that a volume fraction of 0.06 can be attained over a 

duration of 0.5 s in both locations at room temperature. Based on the above reasoning, the 

current nacelle simulator mimics some of the operational features of a real nacelle. 

0

5

10

15

20

0 5 10 15 20 25 30

Room temperature release, aft port

Room air / Cold agent release, aft port

Cold temperarure release, aft port

Volume Fraction (%)

Time (s)

Figure 5. Concentration profiles of CF3I at the aft measurement location under three test

conditions.

For cold temperature release (both agent and air at –40 oC), the off-resonance spectral 

measurements at 500 nm did not indicate the initial presence of droplets at both forward and aft 

measurement locations. The absence of the droplets was due partly to the reduction in the initial 

bottle pressure (≈ 3 MPa –40 oC vs. ≈ 4.1 MPa at room temperature), which would impart less 

momentum to the droplets upon the release of the agent. Droplets with less momentum were less 

9
likely to be transported to the two measurement locations. The combined effect of low bottle

pressure and large liquid fraction in cold temperature release might generate larger droplets as a 

result of poor atomization of the liquid core, thus hindering the droplets from following the 

airflow. Similar to the room temperature release, the concentration at the forward location was

higher than that at the aft. However, the difference was not as significant as in the case of room 

temperature release. The most important finding from this study was that there was a significant 

reduction in the agent concentration in the cold temperature release. At the forward 

measurement location, a reduction of a factor of almost 3 was observed at the peak 

concentration. At both locations, the agent concentration measurements were always below a 

volume fraction of 0.06. 

Another set of experiments has also been carried out using agent at –40 oC and airflow at room 

temperature. The results are also shown in Figures 4 and 5. An initial spike was again observed 

at the forward measurement location, an indication of the presence of droplets. The 

concentration distributions under these conditions are intermediate between the room and cold

temperature releases. The room temperature airflow improves the dispersion and evaporation of 

the cold agent to a certain extent. 

CONCLUSIONS 

Discharge tests have been conducted at –40 oC in an aircraft engine nacelle simulator placed 

inside an environmental test chamber. The temperatures of the airflow and the agent were found 

to have a significant effect on the subsequent dispersion of the agent upon its release. 

Comparing to the observations from room temperature discharge tests, the results at –40 oC from 

the two measurement locations in the nacelle have shown that the dispersion of CF3I under this

condition is not very effective and there is substantial deterioration in agent concentration. If the 

required agent extinguishing concentration for the engine nacelle is based on room temperature 

test data, the effect of using the agent at a temperature much lower than its normal boiling point 

must be accounted for. 

ACKNOWLEDGEMENTS 

This research is part of the Department of Defense’s Next Generation Fire Suppression 

Technology Program (NGP), funded by the DoD Strategic Environmental Research and 

Development Program (SERDP). Dr. Richard G. Gann of the National Institute of Standards and

Technology (NIST) is the technical program manager. We would also like to thank Dr. Vladimir

Orkin of the Chemical Sciences and Technology Laboratory (CSTL) of NIST for providing the 

calibration facility and his assistance in the calibration of the UV spectrometer and Dr. William

L. Grosshandler of our laboratory for many stimulating discussions and encouragement. SLM

also acknowledges the financial support from the National Research Council Postdoctoral 

Research Associateship.

REFERENCES

[1] Military Specification, MIL-E-22285 (Wep). Extinguishing System, Fire, Aircraft, High10
Rate-Discharge Type, Installation and Test of, 11 December 1959, Amendment – 1, 27 

April 1960. 

[2] Grosshandler W.L., Gann R.G., and Pitts W.M. (eds.), Evaluation of Alternative in-Flight 

Fire Suppressants for Full-Scale Testing in Simulated Aircraft Engine Nacelles and Dry

Bays, NIST SP 861, April 1994, U.S. Department of Commerce, Washington, DC. 

[3] Gann R.G. (ed), Fire Suppression System Performance of Alternative Agents in Aircraft 

Engine and Dry Bay Laboratory Simulations, Volumes. I and II, NIST SP 890, U.S. 

Department of Commerce, Washington, DC, November 1995. 

[4] Yang, J.C., Cleary, T.G., Vazquez, I., Boyer, C.I., King, M.D., Breuel, B.D., Womeldorf, 

C.A., Grosshandler, W.L., Huber, M.L., Weber, L., and Gmurczyk, G., “Optimization of 

System Discharge,” in Chapter 8, Fire Suppression System Performance of Alternative 

Agents in Aircraft Engine and Dry Bay Laboratory Simulations, Vol. I, Gann, R.G. (ed.), 

NIST SP 890, U.S. Department of Commerce, Washington, DC, November 1995. 

[5] Smith, B.D. and Srivastava, R. Thermodynamic Data for Pure Compounds, Part B, 

Halogenated Hydrocarbons and Alcohols, Elsevier, Amsterdam, 1986. 

[6] NIST Thermodynamic Properties of Refrigerants and Refrigerant Mixtures Database 

(REPROP), V.4.0, NIST Standard Reference Data Program #23, NIST, Gaithersburg, MD, 

1993. 

[7] Guesto-Barnak, D., Sears, R., Simpson, T., “Engine nacelle fire protection using non-ozone 

depleting fire suppressants,” Proceedings of International Conference on Ozone Protection

Technologies, pp. 515-524, Washington, D.C., October 21-23, 1996. 

[8] Meserve, W.J. Personal communication. Pacific Scientific, HTL/KIN-Tech Division, 

Document Number 51750579, Duarte, California, May 2000. 

[9] Yang, J.C., Nyden M.R., and Manzello, S.L., “Cold Discharge of CF3I in a Simulated 

Aircraft Engine Nacelle,” Proceedings of Halon Options Technical Working Conference, 

Albuquerque, New Mexico, 24-26 April 2001. 

[10] Hamins, A, Cleary, TG, Borthwick, P, Gorchkov, N, McGrattan, K, Forney, G, 

Grosshandler, WL, Presser, C, and Melton, L., “Suppression of Engine Nacelle Fires,” in 

Chapter 9, Fire Suppression System Performance of Alternative Agents in Aircraft Engine 

and Dry Bay Laboratory Simulations, Vol. II, Gann, R.G. (ed.), NIST SP 890, U.S. 

Department of Commerce, Washington, DC, November 1995. 

[11] DeMore, W.B., Sander, S.P., Golden, D.M., Hampson, R.F., Kurylo, M.J., Howard, C.J., 

Ravishankara, A.R., Kolb, C.E., Molina M.J., “Chemical Kinetics and Photochemical Data 

for Use in Stratospheric Modeling, Evaluation Number 12,” JPL Publication 97-4, January 

15, 1997, Jet Propulsion Laboratory, California Institute of Technology, Pasadena, 

California. 

11