N A s A T E C H N I

M E M O R

C A L A N E u iv7

NASA T M

P R E D I C TI 0 hT OF E N G I N E EX XL4 c! S'T Lviu LELV i nA i iv i~ 3 uu w LY w IIY u I I L V ~ ~ ~ - - m T--= T m n A m - - r n m T c - n n x v r n n v r T h T n CD n n K

THE DELTA-THOR TELSAT-A LAUNCH OF NOVEMBER 9, 1972

N A T I O N A L A E R O N A U T I C S A N D SPACE A D M I N I S T R A T I O N W A S H I N G T O N , D. C. NOVEMBER 1973

https://ntrs.nasa.gov/search.jsp?R=19740002470 2019-02-02T20:57:01+00:00Z

2. G O V E R N M N T ACCESSION NO. I . REPORT NO.

NASA TM X-2939 8 . T l T L E AND SUBTITLE

Prediction of Engine Exhaust Concentrations Downwind from

3. RECIPIENT'S CATALOG NO.

5. REPORT DATE November 1973

I

9. PERFORMING ORGANIZATION NAME AND ADDRESS 10. WORK UNIT NO.

George C. Marshall Space F l igh t Center Marshall Space Fl ight Center, Alabama 35812

7. AUTHOR(S) . John W. Kaufman, Michael Susko, C. Kelly H i l l

11. CONTRACT OR GRANT NO.

Mi20 8. PERFORMING ORGAN1 ZATION REPOR r

3. TYPE OF RkPORi' PERIOD COVEREC

12. SPONSORING AGENCY NAME AND ADDRESS

National Aeronautics and Space Administration Washington, D. C. 20546

I 15. SUPPLEMENTARY NOTES

16. ABSTRACT

Presented i n t h i s report a re the r e s u l t s of the downwind concentrations of engine exhaust by-products from the Delta-Thor Telsat-A vehicle launched from Cape Kennedy, Florida on November 9, 1972 (2014 EST). which exis ted a r e iden t i f i ed a s w e l l as the exhaust cloud rise and the r e s u l t s from the MSFC Multilayer Diffusion Model calculations. compared t o exhaust cloud sampled data acquired by the Langley Research Center personnel. hydrochloric acid ( H C l ) , carbon monoxide (CO) , or aluminum oxide (A1203) reached the ground.

The meteorological conditions

These predictions a re herein

Values of the surface level concentrations show tha t very l i t t l e

*A companion report i s being prepared by Langley Research Center personnel e n t i t l e d "Effluent Sampling of Scout D and Delta Launch Vehicle Exhaust" by William C. Hulten, Richard W. Storey, J r . , Gerald L. Gregory, David C. Woods, and Franklin S. Harr is . , Jr . The report w i l l be avai lable i n the very near future.

.

7 . KEY WORDS Vehicle exhaust diffusion Exhaust cloud dispersion

19. SECURITY CLASSIF. (d thls t o p e ) 20. SECURITY CLA

18. DlSTRleUTlON STATEMENT

Category 12

- 4 F. (of thtm - io ) 121. NO. OF PAGES 122. PRICE

I 49 Domestic, $3.00 I Foreign, $5.50 I UNCLASSIFIED UNCLASSIFIED

I I - -. ___

For sale by National Technical Information Service, Springfield, Virginia 221 51

ACKNOWLEDGEMENT

This document p r e s e n t s work done by pe r sonne l of t h e Atmospheric Dynamics Branch (%E-AERO-YA) of t h e Aerospace Environment ,Divis ion, Aero-Astrodynamics Labora to ry , Marsha l l Space F l i g h t C e n t e r , Alabama. Much c r e d i t must be g iven t o D r s . Leonard L. DeVries and J. Br iscoe Stephens of t h e Aerospace Environment D i v i s i o n who c o n t r i b u t e d

t h e H.E. Cramer Company, S a l t Lake C i t y , Utah, made s i g n i f i c a n t con- t r i b u t i o n s t o t h i s o v e r a l l e f f o r t .

- 5 , 1 e a L ~ y n- ,. I L 1 -- to this e f f o r t . Messrs. K . K . Dumbauld and J a y R. Bjorklund of

M r . Archie L. Jackson of t h e Computational Labora tory (Code S&E-AERO-RRP/MSFC) d i d a g r e a t amount of work computing t h e r e s u l t s , Also thanks t o Messrs. John P. Mugler, Jr . , S c o t t Wagner, Gerald L. Gregory, Dewey E . Wornom, and o t h e r s of t h e Langley Research Center f o r t h e i r c o n s t r u c t i v e c r i t i q u e o f t h e i n i t i a l copy o f t h i s r e p o r t .

ii

TABLE OF CONTENTS

S E C T I O N 1.

1.1

1.2

1 .3

SECTION 2 .

SECTION 3.

SECTION 4.

4.1

4.2

4.3

SECTION 5.

5.1

5.2

SECTION 6 .

APPENDIX.

INTRODUCTION

B a c k g r o u n d ........................................ 2

Propellant P rope r t i e s and V e h i c l e R i s e D a t a ....... 2

O r g a n i z a t i o n of the Technical M e m o r a n d u m .......... 4

-

METEOROLOGICAL MEASUREMENTS FOR THEl DELTA-THOR TELSAT-A LAUNCH ................................... 5

CLOUD R I S E CALCULATIONS ........................... 7

CLOUD DIMENSIONS AND VERTICAL D I S T R I B U T I O N O F

LAUNCH EXHAUST PRODUCTS FOR THE DELTA-THOR TELSAT-A

D i m e n s i o n s of the E x h a u s t C l o u d a t S t a b i l i z a t i o n .. 9

C a l c u l a t i o n of the V e r t i c a l Source S t rength ....... 10

11 Surface C l o u d ..................................... MSFC MULTILAYER D I F F U S I O N MODELS

M o d e l I ........................................... 12

M o d e l 5 or 4, r e spec t ive ly ........................ 1 2

RESULTS OF THE CALCULATIONS ....................... 14

CONCLUSIONS ....................................... 17

METEOROLOGICAL AND SOURCE MODEL I N P U T S ............ 31

REFERENCES ........................................ 37

iii

LI ST OF ILLUSTRATIONS

Figure T i t l e Page

1. A l t i t u d e o f t h e Delta-Thor Telsat-A Vehicle a s a Function of a f t e r I g n i t i o n ................................. 18

- 2. V e r t i c a l P r o f i l e of Temperature and Wind Speed ( s o l i d l i n e s ) from t h e Rawinsonde Released a t Launch Time ....... 19

3 . Temperature and Wind Speed Measured on t h e NASA 150 Meter Ground Wind Tower a t Launch Time ............... 20

4. Wind D i r e c t i o n Measurements from a Rawinsonde and Tower Data on November 9 , 1972 a t 2018 EST ..................... 21

5 . Calcu la t ed Dimensions of t h e S t a b i l i z e d Cloud o f Exhaust Products f o r t h e November 9 , 1972 Launch of a Delta-Thor Vehic le . Height of t h e Cloud Cent ro id i s 747 Meters ............................. 22

6 . C e n t e r l i n e H C l Concen t r a t ions a t t h e Sur face and a t t h e Heights Flown by t h e Sampling A i r c r a f t f o r t h e Delta-Thor Telsat-A Launch o f November 9 , 1972 and f o r t h e Surface I n v e r s i o n Case ....................... 23

7 . C e n t e r l i n e HC1 Concen t r a t ions a t t h e Sur face and a t t h e Heights Flown by t h e Sampling A i r c r a f t f o r t h e Delta-Thor Telsat-A Launch o f November 9 , 1972 and f o r t h e No Sur face - Inve r s ion Case .................... 24

8. C e n t e r l i n e CO Concen t r a t ions a t t h e Sur face and a t t h e He igh t s Flown by t h e Sampling A i r c r a f t f o r t h e Delta-Thor Telsat-A Launch o f November 9 , 1972 and f o r t h e Sur face - Inve r s ion Case ....................... 25

9. C e n t e r l i n e CO Concen t r a t ions a t t h e Sur face and a t t h e Heights Flown by t h e Sampling A i r c r a f t f o r t h e Delta-Thor Telsat-A Launch of November 9 , 1972 and f o r t h e No Sur face - Inve r s ion Case .................... 26

10. C e n t e r l i n e A 1 0 Concen t r a t ions a t t h e Sur face and a t t h e Hezgzts Flown by t h e Sampling A i r c r a f t f o r t h e Delta-Thor Telsat-A Launch of November 9 , 1972 and f o r t h e No Sur face - Inve r s ion Case ............... 27

i v

L I S T OF ILLUSTRATIONS (Continued)

F i g u r e T i t l e Page

11. C e n t e r l i n e A1203 Concent ra t ions a t t h e Sur face and a t t h e Heights Flown by t h e Sampling A i r c r a f t for t h e Delta-Thor Telsat-A Launch o f November 9 , 1972 and f o r t h e Sur face - Inve r s ion Case ..................... 28 ..

12. R i s e Rate of Exhaust Cloud Versus T i m e f o r De l t a - Thor Telsat-A Launch on November 9 , 1972 (2014 EST) a t Cape Kennedy, F l o r i d a 29 ..................................

13. H o r i z o n t a l Growth of Ground Cloud Versus Time f o r Delta-Thor Telsat-A Launch on November 9 , 1972 (20142) a t Cape Kennedy, F l o r i d a 30 ...............................

..

V

LIST OF TABLES

Table T i t l e Page

1. P r o p e l l a n t P r o p e r t i e s of t h e Del ta-Thor F i r s t - S tage ........... ......................................... 3

2 . Sampling A i r c r a f t A l t i t u d e s and T ime of Cloud P e n e t r a t i o n .............................................. 14

vi

DEFINITION OF SYMBOLS

Symbo 1

F C

F I

Q

F Q

E f ini t : ion ---.-

- - buoyancy f l u x

- - gQF TTpC T

P

- - i n i t i a l buoyancy t e r n

pe rcen tage by weight of p o l l u t a n t m a t e r i a l i n t h e f u e l from Table 1

r e s p e c t i v e h e a t con ten t s of l i q u i d and s o l i d f u e l s

dep th of t h e s u r f a c e mixing 1 2 y e r

molecular weight

ambient p r e s s u r e (nb)

i n t e g r a l of t h e Gausslan p r o b a b i l i t y f u n c t i o n between minus i n f i n i t y and t h e to? of t h e I-:-th l a y e r z

TI(

t o t a l weight of exhaust p roduc t s i n t h e s t a b i l i z e d exhaus t c loud

ra te of h e a t r e l e a s e d by burn ing f u e l

H O W f H O W L L S S

v i i

.

DEF I NIT ION OF SYMBOLS ( c o n t i n u e d )

Symbol

QI

QK

QR

wL’ws

T

z

C P

g

r R

t H

.\ t R

t Z R m I

- U

z

2 ’

D e f i n i t i o n

e f f e c t i v e h e a t r e l e a s e d ( c a l )

source s t r e n g t h i n u n i t s of mass pe r u n i t dep th of the K-th l a y e r

f u e l expend i tu re r a t e from Table 1

ambient a i r t empera ture (OK)

r e s p e c t i v e f u e l e x p e n d i t u r e r a t e s f o r l i q u i d and s o l i d f u e l

h e i g h t above ground of any s e l e c t e d l a y e r

s p e c i f i c h e a t of a i r a t c o n s t a n t p r e s s u r e c a l / (OKgm)

g r a v i t a t i o n a l a c c e l e r a t i o n (9 .8 m/sec ) 2

i n i t i a l c loud r a d i u s a t t h e s u r f a c e

s t a b i l i t y parameter

t ime of l a y e r breakdown

time a f t e r i g n i t i o n r e q u i r e d f o r t h e c loud t o r e a c h t h e s t a b i l i z a t i o n h e i g h t

t ime a f t e r i g n i t i o n i n seconds

time i n seconds r e q u i r e d f o r t h e v e h i c l e t o r e a c h the h e i g h t z of maximum r ise of t h e ground cloud

m I (ob ta ined from Equat ion 1)

mean wind speed

h e i g h t o f s t a b i l i z e d c loud

midpoint of t h e K-th l a y e r

v i i i

DEFINITION OF SYMBOLS (continued)

Z BK

z BL

Z L

Z mC

Z mI

TK Z

z TL

Z R

Y C

v I

0 xK

XLK a

CK3 YO

height of the base of the K-th layer

height of the base of the L-th layer

height in the L-th layer at which the concen- tration is calculated

maximum height of cloud rise for a continuous source

maximum rise for an instantaneous source

height of the top of the K-th layer

height of the top of the L-th layer

altitude above the pad in meters

entrainment constant (continuous)

entrainment constant (instantaneous)

standard deviation of the concentration distribution of the stabilized ground cloud

standard deviation of the alongwind concentration distribution in the K-th layer at distance x

standard deviation of the alongwind concentration distribution in the L-th layer for the source originating in the K-th layer

standard deviation o f the alongwind concentration distribution in the K-th layer at cloud stabilization

standard deviation of the crosswind concentration distribution in the K-th layer at cloud stabilization

ix

Symbo 1

a' [Kj 20

a Y M

z LK 0

0

x P

DEFINITION OF SYMBOLS (Continued)

D e f i n i t i o n -- - - s tanddrd d e v i a t i o n o f t h e v e r t i c a l c o n c e n t r a t i o n

d i s t r i b u t i o n i r ; t h e K-th l a y e r a t cloc;d S t B h i L F z - ? t icr.

- - s t a n d a r d d e v i a ' i i o n o f t h e c rc~ss i i i nc~ c o n c c n t r a t i o i i distribution i n tht. K- th layer a t u i s t s n c e x

- - s t a n d s r d cic-viation o f t he crosswind c o n c e n t r a t i o n c l i s t r i b u t i o z ir, the-: L-th la::^: f o r t?,,e s o u r c e o r i g i n a t i n g i n t he I<-th l z y e r

- - s t anda rd d e v i a t i o n o< t h e v e r t i c a l c o n c e n t r a t i o n d i s t r i b u t i o n i n t h c L - t h Layer f c r t h c s c u r c e o r i g i n a t i n g i n t h e K-th l a y e r

- - d e n s i t y oi a x b i e n t a i r ( g / m 3 )

- - v e r t i c a l g rad ie r i t o f anbierit ;>ot;.ntial temperz- t u r e

peak or c e n t e r l i n e concen t r ac lon - -

X

John W. Kaufman Michae 1 Susko C. Kel ly H i l l

SUMMARY

The s t u d y of t h e eng ine exhaus t by-products from the Delta-Thor Telsat-A v e h i c l e has made a s i g n i f i c a n t c o n t r i b u t i o n t o t h e unde r s t and ing of t h e dynamics of such h o t buoyant c louds. P r e d i c t i o n s made o f t h e ground c loud r i s e were s a t i s f a c t o r y and the d i s p e r s i o n c h a r a c t e r i s t i c s were c a l c u l a t e d . Although t h e emis s ion source from t h e Delta-Thor i s l i m i t e d due t o t h e sma l lnes s of t h e v e h i c l e a s u f f i c i e n t amount of d a t a were a v a i l a b l e t o s t u d y t h e behavior of exhaus t m a t e r i a l i n t h e a tmospher ic mixing l a y e r . I n t h a t t h e c a l c u l a t i o n s show t h e maximum c e n t e r l i n e peak c o n c e n t r a t i o n s o f HC1 were o n l y abou t 1.0 ppm, no r e a l t o x i c c o n d i t i o n could have r e s u l t e d .

A d d i t i o n a l work should be done to examine t h e behavior of f u t u r e Delta-Thor exhaus t emiss ions and o t h e r v e h i c l e exhaus t s t o p r o p e r l y unde r s t and t h e atmospheric d i f f u s i o n of such e f f l u e n t s . This i s needed t o de te rmine launch c o n s t r a i n t s f o r a l l v e h i c l e s which emi t nu i sance t y p e exhaus t by-products.

.

SECTION 1. INTRODUCTION

John W. Kaufman Michae 1 Susko C. K e l l y H i l l

1.1 Background

Estimates have been made o f t h e exhaus t emis s ion c o n c e n t r a t i o n s downwind from t h e Delta-Thor Telsat-A v e h i c l e launched-on November 9 , 1972 from Cape Kennedy. M u l t i l a y e r D i f f u s i o n Models 1 & 5 [l] o r Models 1 and 4 of t h e r e v i s e d r e p o r t [2]. CO, and A 1 2 0 3 . and a t h e i g h t s above ground co r re spond ing t o t h e f l i g h t a l t i t u d e s a t which t h e sampling a i r c r a f t o p e r a t e d by Langley Research Center p e n e t r a t e d t h e d i f f u s i n g ground cloud. Source d a t a used i n d e r i v i n g source model i n p u t s were ob ta ined from pe r sonne l a t MSFC and Langley Research C e n t e r , and from t h e eng ine manufac tu re r s . Me teo ro log ica l d a t a used i n t h e c a l - c u l a t i o n s were ob ta ined from a rawinsonde r e l e a s e d from Cape Kennedy n e a r t h e t i m e o f t h e launch and from measurements made on t h e NASA 150 Meter Ground Wind Tower a t KSC [3].

The r e s u l t s were o b t a i n e d by u s i n g t h e MSFC

Compounds from t h e s o l i d r o c k e t eng ines of concern were HC1, P o l l u t a n t c o n c e n t r a t i o n s were c a l c u l a t e d a t ground l e v e l

1 . 2 P r o p e l l a n t P r o p e r t i e s and Veh ic l e R i s e Data

The f i r s t s t a g e of t h e Delta-Thor T e l s a t - A v e h i c l e used i n t h i s launch was comprised of a l i q u i d - f u e l e d eng ine and s i x s o l i d - f u e l s t r a p - o n engines . P r o p e l l a n t p r o p e r t i e s o f t h e Delta-Thor eng ines a r e shown i n Table 1. The p r o p e l l a n t e x p e n d i t u r e s ra tes g i v e n i n t h e t a b l e a r e average r a t e s over t h e t o t a l burn t i m e s shown i n Table 1. The p r o p e l l a n t h e a t c o n t e n t s i n Table 1 a r e based on e s t i m a t e s o b t a i n e d from t h e eng ine manufac tu re r s , and do n o t i n c l u d e h e a t gene ra t ed by recombina t ion of chemical r a d i c a l s as t h e exhaus t c loud c o o l s t o ambient t empera tu re o r The h e a t due t o k i n e t i c energy . The p r o p e l l a n t h e a t c o n t e n t s i n t h e t a b l e were used i n t h e c a l c u l a t i o n s o f c loud r i s e , and it was found t h a t t h e s e d a t a were i n good agreement w i t h e x i s t i n g measurements from l i q u i d - f u e l e d and s o l i d - f u e l e d exhaus t emiss ions [ 4 th rough 141. should be n o t e d , however, t h a t c loud r ise measurements were n o t a v a i l - a l b e f o r launches of v e h i c l e s w i t h f i r s t s t a g e s comprised of bo th l i q u i d - and s o l i d - f u e l e d eng ines .

It

The a l t i t u d e - t i m e curve of t h e Delta-Thor Telsa t -A i s a l s o r e q u i r e d to compute t h e r ise o f t h e ground c loud of exhaus t p roduc t s . F igure 1 shows a p l o t of v e h i c l e a l t i t u d e v e r s u s t i m e a f t e r i g n i t i o n . A l oga r i thmic l e a s t - s q u a r e s r e g r e s s i o n curve f i t t e d t o t h e d a t a shown i n Figure 1 y i e l d s t h e e x p r e s s i o n

0.39457 t R = 1.32095~R 2

TAETLE 1.

PROPELLANT PROPERTIES OF THE DELTA-THOR PIRST-STAGE;k

P r o p e l l a n t Expendi ture Rate ( g / s e c )

Liquid Engine

S i x S o l i d Motors

T o t a l Burn Time ( s e c )

Liquid Engine

S o l i d Motor

P r o p e l l a n t Heat Content ( c a l l g )

Liquid P r o p e l l a n t

S o l i d P r o p e l l a n t

P r o p e l l a n t Composition (pe rcen t by weight )

Liquid P r o p e l l a n t

co

So l id P r o p e l l a n t

HC 1

co

A1 0 2 3

5

5

3.13256 x 10

6.04367 x 10

212

37

500

6 9 1

47.30

20.83

22.26

37.77

*Data were ob ta ined through p e r s o n a l communication w i t h United Technology Center D i v i s i o n of United A i r c r a f t , Sunnyvale C a l i f o r n i a , November 1972.

3

which r e l a t e s t h a t t h e t ime a f t e r l i f t o f f ( t R ) i s a f u n c t i o n o f t h e a l t i t u d e o f t h e v e h i c l e above pad (2,).

1 . 3 Organ iza t ion of t h e Techn ica l Memorandum

S e c t i o n 2 c o n t a i n s a d e s c r i p t i o n of t h e m e t e o r o l o g i c a l measure- ments made a t t h e time of t h e Delta-Thor Telsa t -A launch on November 9 , 1972. S e c t i o n 3 d e s c r i b e s t h e c loud r i s e c a l c u l a t i o n s f o r t h e launch.

t h e ground-cloud produced by t h e Delta-Thor Telsat-A launch a r e d i scussed i n Sec t ion 4 . The MSFC M u l t i l a y e r D i f f u s i o n Models used i n t h e c a l c u l a - t i o n o f c o n c e n t r a t i o n s downwind from t h e launch a r e b r i e f l y desc r ibed i n Sec t ion 5. The r e s u l t s of t h e c a l c u l a t i o n s a r e g i v e n i n S e c t i o n 6 .

The c lnud dimen.icns 2nd Tv7erticll distributien ef e-,hal;st pr=dl;cts in

4

SECT ION 2. METEOROLOG I CAL MEASUREMENTS FOR THE DELTA-THOR LAUNCH

Rawinsonde measurements w e r e made a t Cape Kennedy throughout t h e day p receed ing t h e launch of t h e Delta-Thor v e h i c l e a t 2014 EST on November 9 , 1972. A l l t h e measurements i n d i c a t e d t h e p re sence of a mar ine i n v e r s i o n over t h e Cape Kennedy a r e a w i t h t h e b a s e of t h e i n v e r s i o n n e a r 900 meters above t h e s u r f a c e and t h e t o p of t h e i n v e r s i o n a t h e i g h t s of 1300 t o 1500 meters. The tempera ture l a p s e r a t e from t h e s u r f a c e t o t h e b a s e of t h e marine i n v e r s i o n w a s approximately d r y a d i a b a t i c through- o u t t h e day. During t h e e a r l y evening , a surface-based i n v e r s i o n began t o form over t h e l and . By 2014 EST, t h i s i n v e r s i o n w a s about 150 meters i n depth . The tempera ture and wind speed p r o f i l e s i n t h e lowes t 2000 meters measured by t h e rawinsonde r e l e a s e d a t 2018 EST are shown i n F igu re 2 . I n s p e c t i o n of F igu re 2 shows that wind speed a t a l l h e i g h t s i n t h e lowes t 2000 meters d i d n o t exceed 4 meters p e r second. A t t h e s u r f a c e , winds were n e a r l y c a l m . Wind speed i n c r e a s e d through t h e s u r f a c e i n v e r s i o n t o 4 meters pe r second a t the top of t h e i n v e r s i o n , t h e n re- mained n e a r l y c o n s t a n t t o t h e h e i g h t of t h e mar ine i n v e r s i o n base . Wind speed decreased w i t h h e i g h t i n t h e marine i n v e r s i o n .

The l aunch s i t e of t h e Delta-Thor v e h i c l e is s i t u a t e d a t t h e s h o r e l i n e two m i l e s s o u t h of t h e l o c a t i o n where t h e rawinsonde i s r e l e a s e d . For t h i s r eason , t h e surface-based i n v e r s i o n i n d i c a t e d by t h e rawinsonde d a t a may n o t have been p r e s e n t above t h e launch s i t e o r below t h e i n i t i a l downwind t r a j e c t o r y of t h e exhaus t c loud . Concen t r a t ions w e r e , t h e r e f o r e , c a l c u l a t e d f o r bo th t h e case where t h e sur face-based i n v e r s i o n w a s p r e s e n t and t h e case where no i n v e r s i o n w a s p r e s e n t . The dashed l i n e s i n F igu re 2 show modi f i ca t ions i n t h e rawinsonde p r o f i l e s used i n t h e c a l c u l a t i o n s where t h e surface-based i n v e r s i o n w a s n o t con- s i d e r e d . The wind speed p r o f i l e w a s modif ied between t h e h e i g h t s of 800 and 1200 meters s o t h e computer program would c a l c u l a t e a mean wind speed i n l a y e r between 200 and 900 meters r e p r e s e n t a t i v e of t h e observed mean wind speed i n t h i s l a y e r .

F igu re 3 shows t h e v e r t i c a l t empera ture and wind speed p r o f i l e s measured a t t h e NASA 150 Meter Ground Wind Tower a t launch t i m e . Th i s tower i s l o c a t e d about 1 3 m i l e s nor th-northwest of Launch Complex 1 7 . These measurements a g r e e w i t h t h e rawinsonde d a t a , and w e r e used t o s p e c i f y t h e wind speed and t empera tu re p r o f i l e s i n t h e lowes t 150 meters f o r t h e case i n which t h e surface-based i n v e r s i o n w a s assumed t o be p r e s e n t a t t h e l aunch s i t e . The v a l u e of t h e 10 minute s t a n d a r d d e v i a t i o n of azimuth wind a n g l e of 9 deg rees used i n the c a l c u l a t i o n w a s ob ta ined from t h e tower measurements.

5

Figure 4 shows t h e wind d i r e c t i o n p r o f i l e measured by the rawinsonde and t h e 150 m Ground Wind Tower a t T+4 minutes . Rapid changes i n t h e l a r g e - s c a l e wind f i e l d were o c c u r r i n g i n t h e lower atmosphere a t t h i s t ime. This c o n d i t i o n p lus some o v e r r i d i n g e f f e c t s of the sea breeze produced a s i t u a t i o n , whereby, wind d i r e c t i o n p r o f i l e d i f f e r e n c e s i n t h e lowest 1 km a l t i t u d e were l i k e l y a c r o s s Cape Kennedy, e s p e c i a l l y , between t h e c o a s t l i n e and p o i n t s i n l a n d . Wi th in t h e marine i n v e r s i o n t h e d i r e c t i o n veered w i t h h e i g h t from 130 degrees a t t h e base t o 230 degrees a t t h e t o p of t h e i n v e r s i o n . The d i r e c t i o n below t h e marine i n v e r s i o n was n e a r l y c o n s t a n t from approximate ly 130 degrees a t the base t o 230 degrees a t t h e t o p of t h e i n v e r s i o n . The d i r e c t i o n below t h e marine i n v e r s i o n was n e a r l y c o n s t a n t from approximate ly 130 degrees w i t h i n t h e 300-900 meter a l t i t u d e l a y e r . Between t h e ground and 300 meters t h e wind veered s h a r p l y from 220 degrees t o about 130 degrees . The wind d i r e c t i o n p r e d i c t i o n of 035 degrees i n t h e ground t o 700 meter l a y e r was v a l i d on ly f o r t h e o r i g i n a l launch t i m e o f 1758 EST. The r a p i d changes i n the wind f i e l d beginning about t h i s t ime made t h e f o r e - c a s t p repared f o r 1758 EST n o t t r u l y a p p l i c a b l e f o r t h e launch a t 2014 EST s i n c e t h e r e was about a 2 hour d e l a y . A t ime-he ight c r o s s - s e c t i o n a n a l y s i s of a sequence of wind p r o f i l e i n d i c a t e s t h a t a wind d i r e c t i o n o f about 050 degrees over t h e rawinsonde s i t e l i k e l y occur red a t t he o r i g i n a l l y scheduled launch t i m e . Thus, t h e p r e d i c t e d 035 degrees compares f avorab ly w i t h t h e analyzed 050 degrees f o r t h e o r i g i n a l launch time wind d i r e c t i o n ; however, t h e f a c t t h a t t h e a c t u a l measured wind d i r e c t i o n a f t e r t h e d e l a y was 130 degrees demonst ra tes t h e c r i t i c a l i t y o f t ime i n a tmospher ic p r e d i c t i o n s . It i s q u i t e reasonable t o expec t from t h i s a tmospheric s i t u a t i o n d e s c r i b e d t h a t t h e exhaus t ground cloud may have d r i f t e d a long a somewhat d i f f e r e n t t r a j e c t o r y t h a n might be i n f e r r e d from a s t r i c t a p p l i c a t i o n of t h e rawinsonde p r o f i l e d a t a .

The me teo ro log ica l i n p u t s used i n t h e c a l c u l a t i o n s a r e g iven , a long w i t h t h e source model i n p u t s d e s c r i b e d i n S e c t i o n s 3 and 4 below, i n the Appendix. The Appendix a l s o c o n t a i n s a d e s c r i p t i o n o f t h e r a t i o n a l e used t o s p e c i f y t h e v e r t i c a l p r o f i l e s of o ~ { T ~ K ] and oE r equ i r ed f o r use i n t h e MSFC M u l t i l a y e r D i f f u s i o n Model Program.

6

SECTION 3, CLOUD R I S E CALCULATIONS

The burn ing of r o c k e t eng ines du r ing normal launches r e s u l t s i n t h e fo rma t ion of a cloud of ho t exhaus t products which subsequen t ly r i s e s and e n t r a i n s ambient a i r u n t i l an e q u i l i b r i u m w i t h ambient c o n d i t i o n s i s achieved . Experience t o d a t e shows t h a t the buoyant r i s e of exhaus t c louds from normal launches o f l a r g e l i q u i d - f u e l e d v e h i c l e s i s b e s t p r e d i c t e d by u s i n g a c loud r i s e model f o r cont inuous sou rces . This i s probably exp la ined by t h e r e l a t i v e l y long v e h i c l e r e s i d e n c e t i m e on t h e pad a f t e r i g n i t i o n and j u s t above the pad. On t h e o t h e r hand, expe r i ence i n p r e d i c t i n g t h e buoyant r ise from normal launches of s o l i d - f u e l e d v e h i c l e s i n d i c a t e s the r i s e i s b e s t p r e d i c t e d u s i n g a cloud r i s e model f o r i n s t a n t a n e o u s sou rces . F o r s o l i d - f u e l e d v e h i c l e s r e s i d e n c e t imes near t h e pad a r e r e l a t i v e l y s h o r t . Measurements of c loud r i s e from launches o f Delta-Thor v e h i c l e s were n o t a v a i l a b l e . S ince the f i r s t - s t a g e of the Delta-Thor v e h i c l e i s comprised of bo th s o l i d - f u e l e d and l i q u i d - f u e l e d e n g i n e s , t h e r e i s some ques t ion which formula, cont inuous o r i n s t a n t a n e o u s , y i e l d s a p p r o p r i a t e cloud r i s e e s t i m a t e s . I n t h i s c a s e , a d e c i s i o n was made t o c a l c u l a t e t h e r i s e u s i n g both formulas and t o use the average of the two a s a n e s t i m a t e of c loud r ise . I n t h e c a l c u l a t i o n of c loud r i s e w i t h t h e two formulas , t h e tempera ture s t r u c t u r e i n d i c a t e d by t h e dashed l i n e s i n F igu re 2 was used , p r i n c i p a l l y because t h e sha l low sur face-based i n v e r s i o n would have l i t t l e e f f e c t i n i n h i b i t i n g c loud r i s e .

The maximum r i s e z f o r an in s t an taneous source i s g iven by m I t h e e x p r e s s i o n

I n d e r i v i n g Equat ion ( l ) , i t i s assumed t h a t t h e i n i t i a l upward momentum imparted t o t h e exhaus t gases by r e f l e c t i o n from t h e ground s u r f a c e and launch pad hardware i s i n s i g n i f i c a n t i n comparison w i t h t h e e f f e c t of thermal buoyancy. Based on l i m i t e d exper ience i n p r e d i c t i n g cloud r i s e from launches a t Vandenberg A i r Force Base, t h i s assumption appea r s t o be j u s t i f i e d . The t i m e r e q u i r e d f o r the cloud t o r e a c h t h e s t a b i i i - z a t i o n h e i g h t i s g iven by the e x p r e s s i o n

r: t = 11 2

S H

7

In c a l c u l a t i n g z from Equat ion (l), t h e i n s t a n t a n e o u s h e a t m I

r e l e a s e d Q i s ob ta ined from t h e r e l a t i o n s h i p I

Q = Q t f Z 3 I F R m I

( 3 )

I n s p e c t i o n o f t h e e q u a t i o n s g iven above r e v e a l s a n i n t e r d e p e n - dence between t h e c a l c u l a t e d maximum cloud r i s e z , t h e h e i g h t over

which t h e p o t e n t i a l t empera ture g r a d i e n t a @ l a z i s measured, and t h e v a l u e o f t [ z used i n o b t a i n i n g Q Thus, t h e f i n a l v a l u e o f maximum cloud r i s e must be found through i t e r a t i o n o f Equat ion ( 1 ) . The he igh t over which a @ / a z i s measured and t h e t ime t { z ] a r e t h u s made

m c o n s i s t e n t w i t h t h e v a l u e o f z

m i

R m I I '

c a l c u l a t e d from tffe model. m I

The maximum cloud r i s e from a cont inuous sou rce z i s g iven by mC

R r - 2 mC

( 4 )

Equat ion ( 4 ) , a s i n t h e case of Equat ion (1) f o r an i n s t a n t a n e o u s s o u r c e , assumes t h e i n i t i a l momentum f l u x imparted t o t h e plume by dynamic f o r c e s can be ignored i n t h e c a l c u l a t i o n o f maximum cloud r i s e . Again, expe r i ence i n c a l c u l a t i n g cloud r i s e f o r normal launches of l a r g e l i q u i d - f u e l e d r o c k e t s and f o r s t a t i c f i r i n g s has shown t h a t t h i s assumpt ion i s r easonab le . Equat ion ( 4 ) must a l s o be i t e r a t e d t o o b t a i n t h e f i n a l v a l u e of z , s i n c e mC must be e s t ima ted over t h e h e i g h t of f i n a l r i s e .

I n t h e c a l c u l a t i o n s , t h e parameter 1: f o r t h e Del ta-Thor T e l s t a t - A R launch w a s s e t t o ze ro , yI w a s se t t o 0.64 , and

s i s t e n c y w i t h expe r i ence i n p r e d i c t i n g c loud r i s e from o t h e r normal v e h i c l e launches. The mean wind speed U i n Equat ion ( 4 ) w a s se t e q u a l t o 3 .3 meters p e r second and t h e v a l u e f o r t h e r used i n bo th c a l c u l a t i o n s w a s 1218 grams p e r cubic meter . The use of Equat ion (1) r e s u l t e d i n a n e s t i m a t e of z

o f 460 meters and t h e use of Equat ion ( 4 ) r e s u l t e d i n an e s t i m a t e o f z o f 1035 meters . The average of t h e s e two e s t i m a t e s , 747 meters, was used a s t h e p r e d i c t e d h e i g h t of t h e c e n t r o i d of t h e s t a b i l i z e d ground cloud i n t h e c o n c e n t r a t i o n c a l c u l a t i o n s and i n t h e c a l c u l a t i o n o f t h e source dimensions and v e r t i c a l d i s t r i b u t i o n o f exhaus t products desc r ibed i n Sec t ion 4 below.

w a s se t t o 0.5 f o r con- ? C

m I C I

8

SECTION 4. CLOUD DIMENSIONS AND VERTICAL DISTRIBUTION OF EXHAUST PRODUCTS FOR THE DELTA-THOR LAUNCH

Source i n p u t s r e q u i r e d f o r the d i f f u s i o n model c a l c u l a t i o n s i n c l u d e t h e s t a b i l i z a t i o n h e i g h t of t h e exhaust c loud and cloud d imens ions , a s w e l l a s t h e v e r t i c a l d i s t r i b u t i o n of exhaust products i n t h e s t a b i l i z e d c loud . S e c t i o n 3 above. The c a l c u l a t i o n of t h e dimensions of t h e s t a b i l i z e d c l o u d and t h e v e r t i c a l d i s t r i b u t i o n of exhaust products i s desc r ibed be low.

The c a l c u l a t i o n of t h e s t a b i l i z a t i o n h e i g h t zm i s desc r ibed i n

4.1 Dimensions o f t h e Exhaust Cloud a t S t a b i l i z a t i o n

F igu re 5 shows t h e c a l c u l a t e d dimensions of t h e s t a b i l i z e d cloud of exhaus t p r o d u c t s f o r t h e launch of the Delta-Thor T e l s t a t - A v e h i c l e on November 9 , 1972. The s t a b i l i z a t i o n he igh t z w a s c a l c u l a t e d t o be 747 meters as d e s c r i b e d i n S e c t i o n 3 above. The g e n e r a l formula used t o ca l cu - l a t e t h e r a d i u s of t h e s t a b i l i z e d c loud a t h e i g h t z i s g iven by t h e ex- p r e s s i o n

m

where Y = ( Y , + Y c ) / 2 = 0.57

Note t h a t f o r z>z t h e minimum r a d i u s of t h e s t a b i l i z e d cloud i s s e t e q u a l t o 200 me te r s .

m’

A s shown i n F igure 5 , t h e atmosphere f o r t h e Delta-Thor Telsat-A launch was d i v i d e d i n t o 11 l a y e r s between t h e s u r f a c e and 2000 me te r s . The lowes t k i l o m e t e r was subdiv ided i n t o a g r e a t e r number of l a y e r s because t h e sampling a i r c r a f t p e n e t r a t i o n s of the exhaus t cloud were l i m i t e d t o a l t i t u d e s below t h i s h e i g h t . The cloud is assumed t o b e symmetrical about a v e r t i c a l a x i s through t h e cloud c e n t r o i d . The alongwind and crosswind source dimensions of t h e cloud i n each of t h e e l e v e n l a y e r s were c a l c u l a t e d under t h e fo l lowing assumptions:

0 The d i s t r i b u t i o n of exhaus t p roduc t s w i t h i n t h e c loud i s Gaussian ( s e e Sec t ion 4.2 below) i n t h e p lane of t h e ho r i zon

0 The c o n c e n t r a t i o n of exhaust products a t a l a t e r a l d i s t a n c e of one r a d i u s from t h e cloud v e r t i c a l a x i s i s 10 pe rcen t of t h e c o n c e n t r a t i o n a t t h e cloud a x i s

9

The alongwind and crosswind source dimensions r e q u i r e d f o r input t o t h e MSFC D i f f u s i o n Models a r e d e f i n e d f o r each l a y e r by

m ; z ' L z ( yz' / 2 . 1 5

where z ' = midpoint of t h e K-th l a y e r

The q u a n t i t i e s z and z a r e , r e s p e c t i v e l y , t he h e i g h t of t h e t o p and base of t h e K-th l a y e r . TK BK

The cor responding v e r t i c a l source dimension f o r each l a y e r was c a l c u l a t e d from t h e e x p r e s s i o n

Equat ion ( 7 ) a p p l i e s t o a r e c t a n g u l a r m a t e r i a l d i s t r i b u t i o n which has been assumed t o apply a long t h e v e r t i c a l i n t h e K-th l a y e r .

The source dimensions CJ cr , and CT c a l c u l a t e d from

Equat ions (6) and ( 7 ) f o r t h e Delta-Thor Telsat-A launch a r e inc luded i n t h e model i n p u t t a b l e s i n t h e Appendix.

xo' yo Z O

4 .2 C a l c u l a t i o n of t h e V e r t i c a l Source S t r e n g t h D i s t r i b u t i o n i n t h e S t a b i l i z e d Exhaust Cloud

The f r a c t i o n o f m a t e r i a l by weight i n each of t h e K l a y e r s F {K] f o r the Delta-Thor Telsa t -A launch was c a l c u l a t e d from t h e e x p r e s s i o n

Q P { z ~ ~ } ; K = l

P {zBK} = i s the i n t e g r a l o f t h e Gauss ian p r o b a b i l i t y f u n c t i o n between

minus i n f i n i t y and t h e base o f t h e K-th l a y e r z

P (ZBK - zmI/o}. Sigma (a) i s e q u a l t o y ( z = zmI} J2.15. and i s e q u a l t o

BK'

10

The MSFC D i f f u s i o n Models descr ibed i n S e c t i o n 5 below r e q u i r e t h a t sou rce s t r e n g t h i n each of t h e K l aye r s be s p e c i f i e d per u n i t h e i g h t . S ince t h e d e s i r e d c o n c e n t r a t i o n u n i t s f o r H C 1 and CO a r e p a r t s per m i l l i o n , t h e complete e x p r e s s i o n f o r t h e source s t r e n g t h model i n p u t f o r t he K-th l a y e r i s

For A 1 2 0 3 , t h e d e s i r e d c o n c e n t r a t i o n u n i t s a r e mi l l i g rams per cubic meter and t h e complete expres s ion f o r source s t r e n g t h i n t h e K-th l a y e r i s

Equat ions ( 8 ) , ( 9 ) , and (10) were used t o o b t a i n t h e model i n p u t v a l u e s of QK f o r t h e v a r i o u s me teo ro log ica l regimes. t a b u l a t e d i n t h e Appendix.

These v a l u e s of Q a r e K

4.3 Surface Cloud

Photographs of t h e s u r f a c e exhaust c loud show t h a t a s i g n i f i c a n t amount of d a r k e r exhaus t e f f l u e n t remained nex t t o t h e ground. A t 10 seconds t h e approximate h e i g h t of t h e cloud was 50 meters and the d iameter was about 200 me te r s . A f t e r 50 seconds, i t was about 250 meters i n h e i g h t and 300 m i n d i ame te r . The gene ra l consensus of op in ion i s t h a t t h i s was c o o l e r exhaus t by-products which were t rapped i n the s u r f a c e i n v e r s i o n where i t was t r a n s p o r t e d downwind. This phenomena i s not uncornwon and i s f r e q u e n t l y wi tnessed t o occur d u r i n g s t a t i c t e s t i n g and launching o f many d i f f e r e n t v e h i c l e s . Subsequent ly , added s t r e s s i s be ing p laced on t h e s tudy of t h e co ld s u r f a c e c louds gene ra t ed from aerospace v e h i c l e exhaus t emiss ions .

11

SECTION 5. MSFC MULTILAYER DIFFUSION MODELS

A s mentioned above, t h e purpose of t h i s s t u d y i s t o c a l c u l a t e c o n c e n t r a t i o n s downwind from t h e launch pad a r e a a t t h e h e i g h t of t h e a i r c r a f t sampling f l i g h t s and a t ground l e v e l f o r t h e Del ta-Thor Telsat-A launch of November 9 , 1972. To make t h e s e c a l c u l a t i o n s , w e have used Models 1 and 5 of t h e MSFC M u l t i l a y e r D i f f u s i o n Models d e s c r i b e d i n d e t a i l hy Dumbauld, e t a l . (1) o r by Models 1 and 4 i n t h e r e v i s e d r e p o r t ( 2 ) . Important f e a t u r e s of t h e Models a r e summarized below. Model 1 has p r i n c i p a l l y been used t o c a l c u l a t e c e n t e r l i n e c o n c e n t r a t i o n s i n the rma l ly s t a b l e l a y e r s and Model 5 and 4 , r e s p e c t i v e l y , have been used t o c a l c u l a t e c e n t e r l i n e c o n c e n t r a t i o n s i n the rma l ly n e u t r a l and u n s t a b l e l a y e r s . The p a r t i c u l a r model used i n e a c h o f t h e K l a y e r s i s i d e n t i f i e d i n t h e model input t a b l e s presented i n t h e Appendix.

--

5.1 Model 1

I n Model 1, t h e source i s assumed t o ex tend v e r t i c a l l y through t h e l a y e r K , t h e v e r t i c a l d i s t r i b u t i o n of m a t e r i a l i s assumed t o be i n v a r i a n t w i t h i n t h e l a y e r , and t h e alongwind and crosswind d i s t r i b u t i o n s o f m a t e r i a l a r e assumed t o be Gaussian. I n a d d i t i o n , a l l t h e m a t e r i a l i n i t i a l l y conta ined i n t h e l a y e r K i s c o n s t r a i n e d from d i f f u s i n g v e r t i c a l l y beyond t h e upper and lower l a y e r boundar ies . A s no ted above, t h i s model has been used i n t h e p r e s e n t s tudy t o c a l c u l a t e p o l l u t a n t c o n c e n t r a t i o n s i n thermal ly s t a b l e l a y e r s .

I n Model 1, t h e peak o r c e n t e r l i n e c o n c e n t r a t i o n i n t h e K-th l a y e r a t some d i s t a n c e x downwind from t h e source i s g iven by t h e e x p r e s s i o n

QK

The subse t of e q u a t i o n s d e f i n i n g o and 0 a r e g iven on pages 14 through 20 of Reference 1 and pages 22 through 26 of Reference 2 . B r i e f l y , cr and CT a r e c a l c u l a t e d by means of s imple power-law

expres s ions r e l a t i n g tu rbu lence parameters t o c loud growth w i t h d i s t a n c e .

YK xK

YK xK

5 . 2 Models 5 o r 4 , R e s p e c t i v e l y

Model 5 o r 4 , r e s p e c t i v e l y ( s e e Sec t ion 5 , 1st pa rag raph) , t h e l a y e r - t r a n s i t i o n model d e s c r i b e d , was p r i n c i p a l l y used t o c a l c u l a t e c e n t e r l i n e c o n c e n t r a t i o n s i n the rma l ly n e u t r a l o r u n s t a b l e l a y e r s because i t provides f o r t h e r e q u i s i t e v e r t i c a l mixing and f o r i d e n t i f y i n g t h e

1 2

c o n t r i b u t i o n of t h e m a t e r i a l conta ined i n each i n i t i a l sub laye r . The forinula e x p r e s s i o n

f o r t h e peak o r c e n t e r l i n e concen t r a t ion i s g iven by t h e

2i ( zTL-zBL)+zTK-zL) + erf r i ( z T L - z B L ) + 2 z BL-'BK-'L

J 2 u zLK A uzLK

-2 i (z TL- z L) +z TK- z L ) + erf( + erf (-2 i (. T L - ~ L) +2 zB L- z B K - ~

zLK 0zLK h a

I n a p p l i c a t i o n , t h e s u r f a c e mixing layer i s f i r s t d iv ided i n t o a number of s u b l a y e r s K t o accommodate t h e v e r t i c a l d i s t r i b u t i o n o f p o l l u t a n t s a s w e l l a s h e i g h t v a r i a t i o n s i n me teo ro log ica l parameters . The m a t e r i a l con ta ined i n t h e s e K l a y e r s i s t h e n al lowed t o mix v e r t i c a l l y a c r o s s l a y e r boundar ies t o form a new l aye r L e q u a l i n dep th t o t h e s u r f a c e mixing l a y e r .

t h e same form a s those used t o d e f i n e OxK,

on pages 26 through 33 o f Reference 1 and on pages 35 through 39 of Reference 2.

a r e of z LK The formulas f o r c a l c u l a t i n g ox= and CT

and 5 and a r e g iven CT z K yK ,

13

SECTION 6. RESULTS OF THE CALCULATIONS

The r e s u l t s of t h e model c a l c u l a t i o n s u s i n g t h e MSFC M u l t i l a y e r D i f fus ion Model Program and t h e m e t e o r o l o g i c a l and source i n p u t s desc r ibed i n the Appendix a r e shown i n F igu res 6 through 11,

Figure 6 shows c e n t e r l i n e HC1 c o n c e n t r a t i o n s f o r t h e model c a l c u l a t F g p L s t h e O U L r * . r f n n c l LaLc-uaacu :--.---- L L l v c L a i u u -- Z - - J ? L ~ I U L C ~ L ~ ~ - -1- by Liie meteoro- l o g i c a l measurements was assumed t o i n h i b i t t h e major p r o t i o n of t h e s t a b i l i z e d ground cloud from d i f f u s i n g t o t h e s u r f a c e . For t h i s r e a s o n , t h e c e n t e r l i n e H C 1 c o n c e n t r a t i o n s a t t h e s u r f a c e a r e v e r y much lower t h a n concen t r a t ions a t h e i g h t s above t h e s u r f a c e i n v e r s i o n and f a l l t o l e s s t han 0 . 1 ppm H C 1 beyond about 2 k i l o m e t e r s from t h e launch pad. F igure 6 a l s o shows c e n t e r l i n e H C 1 c o n c e n t r a t i o n s a t t h e t h r e e h e i g h t s (396m, 701m, and 914m) where t h e sampling a i r c r a f t p e n e t r a t e d t h e s t a b i l i z e d cloud o f exhaus t p roduc t s . Table 2 shows t h e t imes and t h e a l t i t u d e s a t which t h e a i r c r a f t sample runs were made acco rd ing t o t h e in fo rma t ion rece ived from M r . S c o t t Wagner o f Langley Research Center .

TABLE 2 .

SAMPLING AIRCRAFT ALTITUDES AND TIME OF CLOUD PENETRATION

A l t i t u d e (m) T i m e Af t e r Launch (seconds)

396 20 29:

701 310

9 14 86 5

: P l o t t e d on F igu res 1 2 and 13

It should be noted t h a t our e s t i m a t e s f o r t h e t i m e r e q u i r e d f o r t h e cloud t o become s t a b i l i z e d a t a h e i g h t of 747 meters i s about 275 seconds. For t h i s r e a s o n , t h e a i r c r a f t may have sampled t h e cloud be fo re t h e cloud s t a b i l i z e d i n t h e sampling r u n beginning a t 202 seconds a f t e r launch. Thus, t h e c e n t e r l i n e c o n c e n t r a t i o n s shown i n F igu re 6 f o r a he igh t o f 396 meters should be r easonab le . I n s p e c t i o n o f F igure 6 shows t h a t t h e r e i s no d i f f e r e n c e between e s t ima ted c o n c e n t r a t i o n l e v e l s a t h e i g h t s of 701 and 914 meters above t h e s u r f a c e .

14

I n c o n t r a s t t o F igure 6 , F igure 7 shows c e n t e r l i n e H C 1 concen- c c L L a L L V L I a -+: ,.n n f o r tfic = = d e l c a l c u l a t i o n < where the sur face-based i n v e r s i o n was assumed n o t t o be p r e s e n t . I n t h i s ca se , m a t e r i a l i n t h e major p o r t i o n of t h e exhaus t cloud i s p e r m i t t e d t o d i f f u s e t o the s u r f a c e , and s u r f a c e c o n c e n t r a t i o n s a r e g r e a t e r than 0 .1 ppm H C 1 t o a d i s t a n c e of about 20 k i l o m e t e r s from the launch pad. Concent ra t ion a t h e i g h t s above t h e s u r f a c e based i n v e r s i o n a r e a l s o lower than t h e c e n t e r l i n e concen- t r a t i o n s a t s i m i l a r h e i g h t s shown i n Figure 6 , because the l a y e r through which t h e c loud can d i f f u s e i s cor respondingly deeper . Thus, a s shown i n F igu re 7 , H C 1 c o n c e n t r a t i o n s a t a l l he igh t s below t h e marine i n v e r s i o n a r e l e s s t h a n 0 . 1 ppm H C 1 beyond about 20 k i lome te r s from t h e launch pad.

F igure 8 and 9 show t h e r e s p e c t i v e c e n t e r l i n e c o n c e n t r a t i o n s o f CO f o r the i n v e r s i o n and no - inve r s ion cases . S i m i l a r l y , F igure 10 and 11 show c e n t e r l i n e c o n c e n t r a t i o n s of A 1 0 for t h e i n v e r s i o n and no- invers ion c a s e s . t h r e e d i f f e r e n t p o l l u t a n t s i s the t o t a l source s t r e n g t h of H C L , C O , and A 1 0 e m i t t e d , t h e s e f i g u r e s show e s s e n t i a l l y t h e same f e a t u r e s a s d e s c r i b e d above f o r HCL.

Because t h e o n l y d i f f e r e n c e gesween t h e c a l c u l a t i o n s f o r t he

2 3

It should be noted t h a t a l l t he r e s u l t s shown i n t h e f i g u r e s a r e based on t h e assumptions t h a t t h e cloud c e n t r o i d i s a t a h e i g h t above t h e s u r f a c e of about 747 meters and t h a t the procedure f o r e s t i m a t i n g t h e v e r t i c a l d i s t r i b u t i o n o f m a t e r i a l i n t he s t a b i l i z e d ground cloud i s v a l c d . Previous expe r i ence i n e s t i m a t i n g concen t r a t ions downwind from v e h i c l e launches has shown t h a t t h e e s t i m a t i o n procedure i s s e n s i t i v e t o t h e s e assumptions i n t h e f i r s t 10 k i l o m e t e r s downwind from t h e sou rce . The d i f f e r e n c e s i n measured and e s t i m a t e d concen t r a t ions nea r t h e cloud c e n t r o i d would not be expected t o be too l a r g e , provided t h e a i r c r a f t p e n e t r a t e d t h e cloud a t i t s c e n t r o i d . Also, t h e c o n c e n t r a t i o n s shown i n t h e f i g u r e s a r e e s t ima ted maximum concen t r a t ions a t t h e i n d i c a t e d h e i g h t s and d i s t a n c e s . a l s o shown t h a t i t i s ex t remely d i f f i c u l t f o r an a i r c r a f t p i l o t t o de te rmine t h e p o s i t i o n of t h e cloud c e n t e r . t h e a i r c r a f t f l i e s through t h e cloud and the response t i m e o f t h e measurement d e v i c e s must be cons idered i n comparing e s t i m a t e d and measured c o n c e n t r a t i o n s .

Experience i n conduct ing sampling programs has

F i n a l l y , t h e speed w i t h which

F igu res 1 2 and 13 show curves a s were f i t t e d t o exhaus t cloud

7ho cameras were u s e d t o take photographs a t a f requency of 2 r i s e r a t e and h o r i z o n t a l growth d a t a e x t r a c t e d from time l apse photo- graphs . frames per second. North about launch pad c e n t e r a t a d i s t a n c e o f 1600 m (5250 f t ) from t h e pad.

One camera was mounted 208 degrees c lockwise from t r u e

15

The second camera was s i t u a t e d a t an ang le of 3 0 3 O c lockwise and a t a d i s t a n c e o f 2820 m (9250 f t ) from launch pad c e n t e r . pos i t i oned t h e camera approximate ly o r thogona l w i t h t h e pad c e n t e r a s t h e common i n t e r s e c t . Data were o n l y t aken from t h e f i l m t o about 4 minutes a f t e r launch i n t h a t t h i s Delta-Thor was a n i g h t t i m e launch and t h e cloud could no t be v e r y w e l l i l l u m i n a t e d by t h e f lood l i g h t s beyimd t h a t time pe r iod . Improvements can be expec ted i n photographing such c louds a t n igh t from t h e expe r i ence ga ined from t h i s f i r s t a t t e m p t .

This arrangement

16

CONCLUSIONS

The Delta-Thor Telsat-A mis s ion launched on November 9 , 1973, a t Cape Kennedy provided t h e o p p o r t u n i t y t o demonstrate t h e u s e f u l n e s s o f t h e MSFC M u l t i l a y e r D i f f u s i o n Model and provide ground l e v e l c o n c e n t r a t i o n s of exhaus t by-products emi t ted du r ing normal v e h i c l e launches . C e n t e r l i n e c o n c e n t r a t i o n s on the ground f o r HC1 exceed .1 ppm o u t t o a d i s t a n c e of 20 km f o r the no s u r f a c e i n v e r s i o n case . F s r bo th CO and A 1 0 t h i s v a l u e of .1 ppm i s p r e d i c t e d o u t t o a lmost 40 km downwind. 2 3

The ground c loud was monitored q u i t e w e l l even though the v e h i c l e was launched a t n i g h t . The use of a l a r g e number of f lood l i g h t s made it p o s s i b l e t o t r a c k and photograph t h e s t a b i l i z e d ground c loud f o r s e v e r a l minutes .

The i n f o r m a t i o n i n t h i s r e p o r t as w e l l a s the many s i m i l a r s t u d i e s a s r e f e r e n c e d makes it convincing t h a t t h e behavior of v e h i c l e exhaus t c louds can be p r e d i c t e d . Subsequent ly , launch v e h i c l e c o n s t r a i n t s t o sa fegua rd a g a i n s t t h e p o s s i b i l i t y of expos ing any l i f e t o e x c e s s i v e dosages of t o x i c exhaus t by-products, can be p r o p e r l y o u t l i n e d . Th i s i s e s p e c i a l l y necessa ry when p lans a r e made t o launch l a r g e v e h i c l e con- f i g u r a t i o n s such a s t h e Space S h u t t l e .

Th i s s tudy has a l s o shown t h a t it i s convenient t o have a s u f f i c i e n t number o f d i f f u s i o n models so t h a t a l l atmospheric c o n d i t i o n s can be cons ide red . I n a d d i t i o n , t h e m u l t i l a y e r concept has added s i g n i f i c a n t r e a l i s m t o t h i s work where a tmospher ic l a y e r s t r u c t u r e s c a n be t r e a t e d .

17

A L T I T U D E , Z R ( m )

3

2

l o 3 - 8

6

4

2

2 10 - 8

6

4

4

1 2 4 6 10 20 40 T I M E , t, ( s e d

6 0

FIGURE 1. ALTITUDE OF THE DELTA-THOR VEHICLE AS A FUNCTION OF TIME AFTER IGNITION.

18

H E I G H T ( k m )

2 .o

1.8

1.6

1.4

1.2

1 .o

0.8

0.6

0.4

0.2

0 14 16 18 20 22 0 2 4 6

T E M P E R A T U R E ("C) WIND SPEED ( m / s e c )

F i g u r e 2. TEMPERATURE AND WIND SPEED DATA ( S O L I D L I N E S ) FROM RAWINSONC'E AND 150 M TOWER DATA A T 2018 EST NOVEMBER 9, 1972. L I N E S REPRESENT MODIF ICATIONS MADE FOR USE I N C/'\LCULATING

BASED INVERSION.

DASHED

GROUND-LEVEL CONCENTRATIONS I N THE ABSENCE OF A DEEP GROUND-

19

H E I G H T ( m )

I I I I I

-

100

80

60

40

20

0

T E M P E R A T U R E ( " C ) WIND SPEE

FIGURE 3 . TEMPERATURE AND WIND SPEED MEASURED ON THE NASA GROUND WIND TOWER A T LAUNCH T I M E .

20

~~

4 m/se

METER

H E I G H T ( k m )

A 2 .0

1.8 --

1.6 --

1.4

1.2

1 .0

0 .8

0 . 6

0.4

0 .2

0

I 1 I I I I 1 1 1 I 1 I 1 - -

- -

-

-- -

-- -

-- - -

-- - - -

-- - - -

-- - - -

-- -

- -

--; I 1 I I I I I I I I I 1 I

2 2 0 2 6 0 300 3 4 0 20 6 0 1 0 0 1 4 0 180 2 2 0 W I N D D I R E C T I O N ( d e q )

F I G U R E 4. WIND D I R E C T I O N MEASUREMENTS FROM RAWINSONDE AND TOWER DATA ON NOVEMBER 9, 1972 A T 2018 E S T

2 1

H E I G H T ( k m )

2.0

1 .8

1.6

1.4

1.2

1 .o

0.8

0.6

0.4

0.2

0

K = l l

K=10

r

600 400 2 0 0 0 200 400 600 800 W I D T H ( m )

FIGURE 5. CALCULATED DIMENSIONS OF T H E S T A B I L I Z E D CLOUD OF EXHAUST PRODUCTS FOR THE NOVEMBER 9, 1 9 7 2 LAUNCH OF A DELTA-THOR VEHICLE. HEIGHT OF THE CLOUD CENTROID IS 747 METERS.

22

HCI C O N C E N T R A T I O N ( p p m )

F I G U R E 6. CENTERLINE H C l CONCENTRATIONS AT T H E SURFACE AND A T THE HEIGHTS FLOWN BY THE SAMPLING AIRCRAFT FOR THE DELTA-THOR LAUNCH OF NOVEMBER 9, 1972 AND FOR THE SURFACE-INVERSION CASE.

23

HCI CONCENTRATION ( ppm )

2

1 o1 0

4

2

I O 0 8

6

4

2

-1 10

D O W N W I N D D I S T A N C E ( m )

FIGURE 7. CENTERLINE H C l CONCENTRATIONS A T THE SURFACE AND A T THE HEIGHTS FLOWN BY THE SAMPLING AIRCRAFT FOR T H E DELTA-THOR LAUNCH OF NOVEMBER 9, 1 9 7 2 AND FOR T H E NO SURFACE-INVERSION CASE.

24

co C O N C E N T R A T I O N ( p p m )

DOWNWIND DISTANCE ( m )

FIGURE 8. CENTERLINE CO CONCENTRATIONS AT T H E SURFACE AND AT T H E HEIGHTS FLOWN BY T H E SAMPLING AIRCRAFT FOR T H E DELTA-THOR LAUNCH OF NOVEMBER 9, 1972 AND FOR THE SURFACE-INVERSION CASE.

25

C O C O N C E N T R A T I O N ( p p m )

D O W N W I N D D I S T A N C E ( m )

FIGURE 9. CENTERLINE CO CONCENTRATIONS A T THE SURFACE AND A T THE HEIGHTS FLOWN B Y THE SAMPLING A IRCRAFT FOR THE DELTA-THOR LAUNCH OF NOVEMBER 9, 1972 AND FOR THE NO SURFACE-INVERSION CASE.

26

AI,O, C O N C E N T R A T I O N ( m g m - 3 )

FIGURE 10. CENTERLINE A 1 2 0 3 CONCENTRATIONS A T THE SURFACE AND AT THE HEIGHTS FLOWN BY THE SAMPLING AIRCRAFT FOR THE DELTA-THOR LAUNCH OF NOVEMBER 9, 1 9 7 2 AND FOR THE SURFACE-INVERSION CASE.

27

D O W N W I N D D I S T A N C E ( m )

F I G U R E 11. CENTERLINE A 1 2 0 3 CONCENTRATIONS A T THE SURFACE AND A T THE HEIGHTS FLOWN B Y THE SAMPLING A I R C R A F T FOR THE DELTA-THOR LAUNCH OF NOVEMBER 9, 1972 AND FOR THE NO SURFACE-INVERSION CASE.

28

600

500

400

300

200

1oc

C

y . ! L PREDICTED CLOUD CENTER

0 I 2 3 4 T I M E ( m i n )

F IGURE 12. EXHAUST CLOUD A L T I T U D E VERSUS T I M E FOR DELTA-THOR TELSAT-A LAUNCH ON NOVEMBER 9 , 1972 (2014 EST) AT CAPE KENNEDY, FLORIDA

29

H O R I Z O N T A L G R O W T H ( m )

600

500

400

300

200

100

0 0

A I R C R A F T P O S I T I O N A T T + 2 0 2 s e c

/

1 3 4 T I M E ( m i n )

F I G U R E 13. HORIZONTAL GROWTH OF GROUND CLOUD VERSUS T I M E FOR DELTA-THOR LAUNCH ON NOVEMBER 9 , 1972 (2014 EST) A T CAPE KENNEDY, FLORIDA.

30

Meteoro log ica l and source model i n p u t s used i n t h e c o n c e n t r a t i o n c a l c u l a t i o n s a r e g iven i n Table A f o r t h e i n v e r s i o n c a s e and i n Table B f o r t h e no - inve r s ion case . The source inpu t s i n t h e t a b l e s were c a l c u - l a t e d u s i n g t h e procedures desc r ibed i n Sec t ions 3 and 4 of t h e t e c h n i c a l memorandum. The r e q u i s i t e v a l u e s o f mean wind speed , wind d i r e c t i o n , tempera ture and p r e s s u r e were obta ined from t h e rawinsonde and tower measurements d e s c r i b e d i n S e c t i o n 2 . Measurements from t h e NASA 150 m Ground Wind Tower d a t a i n d i c a t e d t h e s tandard d e v i a t i o n of t h e azimuth wind ang le f l u c t u a t i o n s f o r a 10-minute per iod a t a h e i g h t of 18 meters was about n i n e degrees . The fo l lowing general r u l e s were used t o s p e c i f y t h e v e r t i c a l p r o f i l e s of t h e azimuth (J~ \ T ~ ~ \ ) and e l e v a t i o n a n g l e f l u c t u a t i o n s .

I n t h e s u r f a c e mixing l a y e r z H : m

(1) I f t h e wind speed i s cons t an t o r dec reases w i t h h e i g h t i s h e l d c o n s t a n t wi th h e i g h t i n t h e l a y e r . ' OA {'loK\

i n t h e l a y e r

A jToK\ is ( 2 ) I f t h e wind speed i n c r e a s e s w i t h h e i g h t , o

dec reased w i t h h e i g h t acco rd ing t o t h e r e l a t i o n s h i p

where p = wind p r o f i l e exponent

- = mean wind s p e e d a t t h e t o p of t h e l a y e r z

U = mean wind speed a t t h e r e fe rence h e i g h t z

TK TK U

- R R

I n l a y e r s above t h e s u r f a c e mixing l a y e r

(1) I f t h e wind speed i s cons t an t o r d e c r e a s e s w i t h h e i g h t i s decreased l i n e a r l y w i t h h e i g h t from t h e

OA /ToK/ i n a s t a b l e l a y e r ,

v a l u e a t t h e base of t h e l a y e r t o a va lue of one degree a t t h e t o p of t h e l a y e r .

31

I x x x

x x x

M

32

l n o o m o u ,

o m m c 9 m l n

r l r ( I I

c

33

m 4 m e de In0 0 0 w o 0 In In F - 0

- l I n I n " d r n d 0 0 F - m

m o In0 F-0 In In ? " 9 0 4 O d m d 0 0 d- 03 w d r l

r-. c.! ,-: 4 d d d O O d d " 0 - o =

0 0 . m w . . * * m * ' o m

0 e o

Trl m d r - r l

x x x uin F-w o w m

x x x

o w mw ww 0 0 m o F-0

N d

0 0 F - m 0 0 . r l d W . F - F - N m 0 . N

m

NIn mIn -In m o w 0 N O r l d r n r l N r l 0 m o

o o m d d m m F - P I . m m . . . . N . . F - N

r l m m N N w d N N m w x x x

I I I

34

rn U .A s

k a, U

; k cd pc

w w m w e o

w m o a w - o

m w m o m m Y

35

( 2 ) I f t h e wind speed i s c o n s t a n t or d e c r e a s e s w i t h h e i g h t i n an u n s t a b l e l a y e r , 0 {T ] i s he ld c o n s t a n t w i t h h e i g h t i n t h e l aye r A OK

( 3 ) I f t h e wind SDeed i n c r e a s e s w i t h h e i g h t i n an . - u n s t a b l e o r s t a b l e l a y e r , 0 { T } i s decreased w i t h t o t h e r e l a t i o n s h i p A OK h e i g h t acco rd ing

( A - 3 )

where - a n ['T&/'BK]

pK - an[ZTK/ZBK] - u = mean wind speed a t t h e base of t h e l a y e r z

BK BK

It should be noted t h a t 0 { T degree.

} i s n o t pe rmi t t ed t o be l e s s t h a n one A OK

Values of t h e s t anda rd d e v i a t i o n of e l e v a t i o n wind a n g l e f l u c t u a t i o n s a r e s e t e q u a l t o (T { T 3 ; t h a t i s ,

A - K

( A - 4 )

where T = r e f e r e n c e time pe r iod over which (T { T ] i s measured

OK A OK T = source f u n c t i o n t i m e i n t h e l a y e r

K

I n t h e c o n c e n t r a t i o n c a l c u l a t i o n s , T f o r normal launches was s e t e q u a l K t o the time t r e q u i r e d f o r t h e exhaus t c loud t o r e a c h s t a b i l i z a t i o n which

i s ob ta ined from Equat ion 2 i n t h e body of t h e r e p o r t . The v a l u e o f t h e d i f f u s i o n parameters and 6 were set e q u a l t o u n i t y i n a l l c a s e s .

H

36

REFERENCES

1. Dumbauld, R. K. , -- e t a l . , 1970: Handbook f o r e s t i m a t i n g t o x i c f u e l haza rds . F i n a l r e p o r t under Cont rac t NAS8-21453, NASA Rpt . CR-6 1326.

2. Dumbauld, R. K . , J. R. Bjork lund , and J . F . Bowers, March 1973:

Report under NASAJMSFC M u l t i l a y e r D i f f u s i o n Models and Computer Program f o r O p e r a t i o n a l P r e d i c t i o n of Toxic Fue l Hazards. Con t rac t No. NAS8-29033. TR-73-301-02.

3. Kaufman, John W . and L e s t e r F. Keene, "NASA's 150-Meter Meteo ro log ica l Tower Located a t t h e Kennedy Space Cen te r , F l o r i d a , " TM X-53699, J anua ry 29, 1968, NASA.

4 . Susko, Michael and John W. Kaufman, "Apollo S a t u r n Engine Exhaust Cloud R i s e and Growth Phenomena During I n i t i a l Launch," paper p re sen ted a t MSFC's Research Achievement Review, Marsha l l Space F l i g h t Center , H u n t s v i l l e , Alabama, December 2 , 1971, NASA,

5. H a r t , W. S . , "Dynamics of Large Buoyant Clouds Generated by Rocket Launches," J . Bas i c Eng., March 1972.

6 . Br iggs , G. A . , "Some Recent Analyses of Plume Rise Observa t ions ,If paper presented a t t h e 1970 I n t e r n a t i o n a l Union of A i r P o l l u t i o n P reven t ion A s s o c i a t i o n s , Atmospheric Turbulence and D i f f u s i o n Labora tory , Na t iona l Oceanic and Atmospheric Admin i s t r a t ion , Oak Ridge, Tennessee, USA, ATDL, N o . 38, 1970.

7. Hanna, S teven R . , "Cooling Tower Plume R i s e and Condensation" paper p re sen ted a t A i r P o l l u t i o n Turbulence and D i f f u s i o n Symposium, Las Cruces, New Mexico, December 7-10, 1971.

8. Smith, Michael R. and Richard E . Forbes , !'Mass-Energy Balance f o r an S-IC Rocket Exhaust Cloud During S t a t i c F i r i n g , " CR-61357, August 4 , 1971, NASA.

9. Church, H. W . , "Cloud R i s e from High-Explosives Detonat ions ," TID-45000 (53rd Ed) UC-41, Heal th & S a f e t y , SC-RR-68-903, Sandia L a b o r a t o r i e s , Albuquerque, June 1969.

10. Tucker , G. L. Maj. , H. E . Malone, and Capt . R. W . Smith, "Atmospheric D i f f u s i o n of Bery l l ium - P r o j e c t Adobe" Report No. AFRPL-TR-70-65, Three Volumes, J u l y 1971, D i rec to r of L a b o r a t o r i e s , A i r Force Svstem Command. ,

37

REFERENCES (Continued)

11. Susko, Michae l , John W. Kaufman, and K e l l y H i l l , "Rise Rate and Growth of S t a t i c T e s t Vehic le Engine Exhaust Clouds," TM X-53782, Aero-Astrodynamics Research Review No. 7 , October 15, 1968, pp 146-166, NASA.

1 2 . Thayer , S c o t t D . , Mar t in W . Chandler , and Roland T. Chu, "Rise and Growth of Space Vehic le Engine Exhaust and Assoc ia ted D i f f u s i o n Models ," CR-61331, J u l y 1970, NASA.

13. Kaufman, John W . , and Michael Susko, "Review o f S p e c i a l D e t a i l e d Wind and Temperature P r o f i l e Measurements," J o u r n a l of Geophysical Research , Vol. 76, No. 27, September 20, 1971.

14. Susko, Michael and John W. Kaufman, "Exhaust Cloud Rise and Growth f o r Apollo S a t u r n Engines , J o u r n a l of S p a c e c r a f t and Rocke t s , May 1973, Vol. 10, No. 5 , pp. 341-345.

15. D a n i e l s , Glenn E . , May 10, 1971: " T e r r e s t r i a l Environment ( C l i m a t i c ) C r i t e r i a Gu ide l ines f o r Use i n Space Vehicle Development, 1971 Revis ion , ' ' NASA TM X-64589.

16. F i c h t l , George H . , J . W. Kaufman, and W. W. Vaughan, C h a r a c t e r i s t i c s o f Atmospheric Turbulence a s Rela ted t o Wind Loads on T a l l S t r u c t u r e s , " Journa l of Spacec ra f t & Rockets , Vol. 6 , pp. 1396-1403, December 1969.

1 7 . F i c h t l , George H. and George E . McVehil, "Longi tudina l and L a t e r a l Spec t r a of Turbulence i n t h e Atmospheric Boundary Layer a t t h e Kennedy Space Center , I t J o u r n a l o f Applied Meteorology, Vol. 9 , No. 1, February 1970, pp 51-63.

18. C l ima t i c A t l a s of t h e United S t a t e s , U. S. Dept. o f Commerce Environmental Sc ience S e r v i c e s A d m i n i s t r a t i o n , June 1968.

19. N a t i o n a l Primary and Secondary Ambient A i r Q u a l i t y S tanda rds , Environmental P r o t e c t i o n Agency, P a r t I1 of F e d e r a l R e g i s t e r , Vol. 36 , No. 84 , A p r i l 1971 (Updated Nov. 1971) .

20. "Guides f o r Short-Term Exposures of t h e P u b l i c t o A i r P o l l u t a n t s , Vol. 11. Guide f o r Hydrogen Ch lo r ide , " Committee on Toxicology of t h e N a t i o n a l Academy o f Sciences - N a t i o n a l Research Counc i l , Washington, D . C . , Aug. 1971.

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