A description is given of conditions of atmospheric temperature and relative humidity under which hydrochloric acid aerosol is expected upon interaction of the proposed space shuttle rocket exhaust products with the atmosphere

Rhein, R. A.

English

NASA Technical Reports Server

N A T I O N A L A E R O N A U T I C S A N D S P A C E A D M I N I S T R A T I O N
Technical Memorandum 33-619
The Formation of Hydrochloric Acid Aerosol From
the Interaction of the Space Shuttle Rocket
Exhaust With the Atmosphere
Robert A. Rhein
PY
J E T P R O P U L S I O N L A B O R A T O R Y
C A L I F O R N I A I N S T I T U T E O F T E C H N O L O G Y
P A S A D E N A , C A L I F O R N I A
June 1, 1973
https://ntrs.nasa.gov/search.jsp?R=19730016415 2020-03-11T19:44:36+00:00Z
N A T I O N A L A E R O N A U T I C S A N D S P A C E A D M I N I S T R A T I O N
Technical Memorandum 33-619
The Formation of Hydrochloric Acid Aerosol From
the Interaction of the Space Shuttle Rocket
Exhaust With the Atmosphere
Robert A. Rhein
J E T P R O P U L S I O N L A B O R A T O R Y
C A L I F O R N I A I N S T I T U T E OF T E C H N O L O G Y
P A S A D E N A , C A L I F O R N I A
June 1, 1973
Prepared Under Contract No. MAS 7-100
National Aeronautics and Space Administration
PREFACE
The work described in this report was performed by the Propulsion
»!«~ f t •}••Division of the Jet Propulsion LaborsCtoryr-'f.r'.j;,.,
 r.
JPL Technical Memorandum 33-619 111
Page intentionally left blank 
CONTENTS
I. Introduction . 1
II. Results and Discussion 1
References 2
FIGURES
1. Aerosol formation for temperature vs relative humidity,
ratio of exhaust products 6 = 1000 3
2. Aerosol formation for temperature vs relative humidity,
ratio of exhaust products 6 = 2154 4
3. Aerosol formation for temperature vs relative humidity,
ratio of exhaust products 6 = 4642 . 5
4. Aerosol formation for temperature vs relative humidity,
ratio of exhaust products 6 = 10^ 6
5. Aerosol formation for temperature vs relative humidity,
ratio of exhaust products 6 = 2. 15 X 10^ 7
6. Aerosol formation for temperature vs relative humidity,
ratio of exhaust products 6 = 4. 64 X 10^* 8
7. Aerosol formation for temperature vs relative humidity,
ratio of exhaust products 6 = 10^ 9
8. Aerosol formation for temperature vs relative humidity,
ratio of exhaust products 6 = 10 , afterburning of
exhaust products included 10
9. Aerosol formation for temperature vs relative humidity,
ratio of exhaust products 8 = 10 , afterburning of
exhaust products included 11
10. Aerosol formation for temperature vs relative humidity,
ratio of exhaust products 6 = 10^, afterburning of
exhaust products included 12
JPL Technical Memorandum 33-619
ABSTRACT
This report describes the conditions of atmospheric temperature and
relative humidity under which hydrochloric acid aerosol is expected upon
interaction of the proposed Space Shuttle rocket exhaust products with the
atmosphere.
vi JPL Technical Memorandum 33-619
I. INTRODUCTION
This report describes the conditions of atmospheric temperature and
relative humidity under which hydrochloric acid aerosol is expected upon
interaction of the proposed Space Shuttle rocket exhaust products with the
atmosphere. This work is part of an overall effort to define the effects of
the Space Shuttle on the environment (Refs. 1 and 2).
II. RESULTS AND DISCUSSION
The conditions of temperature and relative humidity that result in
hydrochloric acid aerosol upon interaction with the Space Shuttle rocket
exhaust products are shown in Figs. 1-10. In Figs. 8-10, afterburning of
CO and H_ is assumed. Each figure corresponds to a mixture (wt %) ratio
L*
of (air)/(exhaust products), designated in each figure by the term Y.
In the figures, the region to the right of each curve represents the con-
ditions where aerosol is not expected. In the region to the left, where
aerosol is expected, the solid lines represent the expected concentration of
HC1 (wt %) in the aerosol and the dashed lines the concentration of aerosol
in the atmosphere in parts per million.
On a typical ground cloud resulting from the Space Shuttle rocket
engines, the estimated weight ratio of (air)/(exhaust) was 10 (Ref. 2).
These curves include the range from 10 to 10 .
Inspection of the figures indicates that aerosol is expected under con-
ditions of cool weather and high humidity. Including the effect of after burn-
ing results in a predicted small increase in the amount of aerosol.
JPL, Technical Memorandum 33-619
REFERENCES
1. Environmental Statement for the Space Shuttle Program. Final State-
ment, National Aeronautics and Space Administration, Washington, D. C. ,
July, 1972.
2. Cramer, H. E. , et al. , Quantitative Assessment of the Environmental
Effects of Rocket Engine Emissions During Space Shuttle Operations at
Kennedy Space Center. Report GCA-TR-72-8-G, GCA Corp. , Salt Lake
City, Utah, February 7, 1972.
JPL Technical Memorandum 33-619
9
5ID
x
LLJ
>
5
uu
100
90
80
70
60
50
40
30
20
10
0
r= 1000
I f I I I I I I I I I I
-351-30 -25 -20 -15 -10 -50 5 10 15 20 25 30 35
TEMPERATURE, °C
Fig. 1. Aerosol formation for temperature vs relative humidity,
ratio of exhaust products 6 = 1000
JPL Technical Memorandum 33-619
100
-30 -20 -10 0 10
TEMPERATURE, °C
30
Fig. 2. Aerosol formation for temperature vs relative humidity,
ratio of exhaust products 6 = 2154
JPL Technical Memorandum 33-619
Q 70 -
x
LLJ
60 -
50 -
40
30
-30 -20 -10 0 10"
TEMPERATURE, °C
20 30
Fig. 3. Aerosol formation for temperature vs relative humidity,
ratio of exhaust products 6 = 4642
JPL Technical Memorandum 33-619
>-
h^
Q
x
LLJ
-30 -20 •10 0 10
TEMPERATURE, °C
20 30
Fig. 4. Aerosol formation for temperature vs relative humidity,
ratio of exhaust products 6 =
JPL Technical Memorandum 33-619
100
t~\ 85 ~
IE
LLJ
LU
75
70
65
•10 0 10
TEMPERATURE, °C
20 30
Fig. 5. Aerosol formation for temperature vs relative humidity,
ratio of exhaust products 6 = 2. 15 X 104
JPL Technical Memorandum 33-619
i
.x
LLJ
80 -
75
-20 •10 0 10
TEMPERATURE, °C
20 30
Fig. 6. Aerosol formation for temperature vs relative humidity,
ratio of exhaust products 6 = 4. 64 X 10**
8 JPL Technical Memorandum 33-619
100
95
5 90
i
X
LU
< 85
80
751 L I I
-30 -20 •10 0 10
TEMPERATURE, °C
20 30
Fig. 1. Aerosol formation for temperature vs relative humidity,
ratio of exhaust products 6 = 10^
JPL Technical Memorandum 33-619
X
UJ
LU
Of
y= 10
AFTERBURNING CO. H
-30 -20 20 30
TEMPERATURE, °C
Fig. 8. Aerosol formation for temperature vs relative humidity,
ratio of exhaust products 6 = 103, afterburning of
exhaust products included
10 JPL Technical Memorandum 33-619
100
95
90
85 -
X
LLJ
OH
80 -
75 -
70 -
65 -
60
y=10
AFTERBURNING CO,
-30 -20 -10 10 20
TEMPERATURE, °C
30
Fig. 9. Aerosol formation for temperature vs relative humidity,
ratio of exhaust products 6 = 104, afterburning of
exhaust products included
JPL Technical Memorandum 33-619 11
100
95
E 90
z>
x
LU
P
< 85
80
75
\
r = i oj
AFTERBURNING CO,
I I I
-30 -20 •10 0 10
TEMPERATURE, °C
20 30
Fig. 10. Aerosol formation for temperature vs relative humidity,
ratio of exhaust products 6 = 10^, afterburning of
exhaust products included
12 JPL Technical Memorandum 33-619
NASA - JPL - Coml., I.A., Calif.


The Formation of Hydrochloric Acid Aerosol from the Interaction of the Space Shuttle Rocket Exhaust with the Atmosphere

Abstract

Similar works

Full text

Available Versions

NASA Technical Reports Server