Deolassified by authority of W A Classification Change Notices 2%- - . -.

'*.-

I

MEASUREMENTS OF PRESSURE DROP WITH NO HEAT ADDITION I

RESEARCH MEMORAN-DUMI 1

ON MOCKUP SEGMENTS OF THE GENERAL ELEC TRIG

AIR-COOLED AIRCRAFT REACTOR -

By Eldon W. Sams and Tibor I?. Nagey

Lewis Flight Propulsion Laboratory Cleveland, Ohio

NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS

WASHINGTON

NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS

RESEARCH MEMORANDUM

MEASUREMENTS OF PRESSURE DROP WITH NO HEAT ADDITION ON MOCKUP SEGMENTS

OF THl3 GENERAL ELFCTRIC AIR-COOLED AIRCRAFT REACTOR

Eldon W . Sams Aeronautical Research S c i e n t i s t

Propulsion Systems

Tibor F. Nagey Aeronautical Research s c i e n t i s t

Propulsion Systems

Approved: &- ~ e r o y V . Humble

Aeronautical Research S c i e n t i s t

Benjamin Pinkel chi&, ate rial and Thermodynamics

Research Division

-

NACA RM E52105

NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS

RESEARCH MEMORANDUM

MEASUREMENTS OF PRESSURE DROP W I T H NO HEAT ADDITION ON MOCKUP SEGMENTS

OF THE GENERAL ELECTRIC AIR-COOLED ALRCRAFT REACTOR

By Eldon W. Sams and Tibor F. Nagey

SUMMARY

An inves t iga t ion was conducted a t t h e NACA Leuis labora tory t o obta in pressure-drop da ta f o r flow of a i r with no heat addi t ion through mockups of two reac to r segments of t h e proposed General E l e c t r i c Company a i r c r a f t r eac to r . Pressure-drop data were obtained over a range of Reynolds numbers from 4000 t o 80,000, a i r i n l e t Mach numbers from 0.02 t o 0.40, i n l e t pressures up t o about 40 inches of mercury absolute, and ambient air temperatures. The r e s u l t s ind ica te t h a t t h e f r i c t i o n f a c t o r s , correc ted f o r entrance, vena contracta, momentum, and e x i t losses , a r e considerably higher at t h e high R repor ted f o r turbulent flow i n smooth pipes.

INTRODUCTION

An air-cooled reac to r is being b u i l t by t h e General E l e c t r i c Company f o r a i r c r a f t propulsion. The proposed reac to r i s a r i g h t c i r c u l a r cylinder approximately 5 f e e t i n diameter and 3 f e e t long, with cooling air passing a x i a l l y through the reac to r . Axially, t h e reac to r i s composed of t e n segments, each 3.5 inches long, with an a x i a l spacing of 0.125 inches between segments. Each reac to r segment is composed of a s e r i e s of con- c e n t r i c r i n g s between which a r e sandwiched t r i angu la r passages. The cooling a i r flows a x i a l l y through these t r i angu la r passages and i s allowed t o expand i n t o t h e 0.125-inch spacing between segments before flowing through t h e next annular segments. The equivalent diameter of each passage i s va r ied a x i a l l y . The mate r i a l forming t h e concentric rings and t h e tri- angular passages i s a s ta in less-s tee l -c lad uranium oxide core, t h e thickness of t h e sandwich being approximately 0.012 inch.

I n view of the complex geometry of ' the a i r - f low passages, predic t ion of t h e air pressure drop i n t h e reactor from da ta ava i l ab le i n t h e l i t e r - a t u r e i s d i f f i c u l t . I n order t o gain some ins igh t i n t o t h e pressure-drop c h a r a c t e r i s t i c s of t h e reac to r , mockups of s m a l l por t ions of t h e f i f t h and t e n t h annular r eac to r segments were t e s t e d by t h e NACA kwis laboratory.

* . * 0 . .

NACA RM ~52105

The t e s t s were conducted over a range of i n l e t Mach numbers from about 0.02 t o 0.40 wi th i n l e t p ressures up t o about 40 inches of mercury abso lu t e a t ambient a i r temperature. The range of Reynolds numbers i n v e s t i g a t e d was from about 4000 t o 80,000 f o r each of t h e t e s t s e c t i o n s . The r e s u l t s of t h e s e t e s t s are presented h e r e i n i n t h e form of curves of average h a l f - f r i c t i o n f a c t o r p l o t t e d a g a i n s t Reynolds number f o r each of t h e t e s t segments. Both measured and c a l c u l a t e d d a t a a r e a l s o presented i n t a b u l a r f o m .

EQUIPMJiTIT AND 1NTRUME.NTATION

Reactor segments. - Two reac to r segments, number 5 and number 10 i n a x i a l spacing of t h e complete reac tor , were t e s t e d ; bo th were f a b r i c a t e d of 0.012-inch shee t aluminum. Figure l ( a ) shows segment number 5, which had f i v e rows of t r i a n g u l a r passages, and f i g u r e l ( b ) shows segment number 10, which had s i x rows of t r i a n g u l a r passages.

P e r t i n e n t geometr ica l c h a r a c t e r s i t i c s f o r t h e two segments a r e pre- s en ted i n t h e fo l lowing t a b l e :

I

A i r system. - A schematic diagram of t h e t e s t s e c t i o n and experimental s e t u p used i n t h i s i n v e s t i g a t i o n i s shown i n f i g u r e 2. F igure 2 ( a ) shows I t h e g e n e r a l p ip ing layout . Serv ice a i r a t 110 pounds pe r square i nch gage I

i s passed through a f i l t e r , through a pressure- regula t ing valve, and then 1 th rcugh an o r i f i c e run, c o n s i s t i n g of an air s t r a i g h t e n e r and an A.S.M.E.- t ype f l a t - p l a t e o r i f i c e where t h e a i r f low i s measured be fo re e n t e r i n g t h e i n l e t tank. From t h e i n l e t tank, the air f lows through t h e t e s t s e c t i o n and i s discharged t o atmosphere. The o r i f i c e and t e s t - s e c t i o n i n l e t - a i r

I temperature i s measured by a thermocouple j u s t downstream of t h e o r i f i c e p l a t e .

I I

Reactor segment number

5

10

Tes t - sec t ion ins t rumenta t ion . - The r e a c t o r segment w a s mounted i n a r e c t a n g u l a r wood duct provided with a rounded en t rance s e c t i o n . Three s t a t i c p re s su re t a p s were loca t ed i n t h e wood duct a t both t h e en t rance , s e c t i o n and t h e e x i t s e c t i o n as shown i n f i g u r e 2(b) ; one t a p was l o c a t e d a t t h e bottom and one t a p on each s ide of t h e duct a t bo th sec t ions . The s t a t i c p re s su re drop was taken as the d i f f e r e n c e between t h e average i n l e t

Length ( i n . )

3.5

3.5

Width ( i n . )

3

3

Height ( i n . )

2

2

Equivalent diameter

( f t )

0.0208

0.0201

Length t o diameter

r a t i o

~ / " e

14.0

14.45

F ree f low a r e a

( s q f t )

0.0385

0.0386

Free-flow f a c t o r

0.92

9.90

N cn t-' Cn

NACA RM E52105 3

and t h e average o u t l e t measured s t a t i c p re s su re s . I n s e v e r a l cases , a s a check on t h e instrumentat ion, t h e s t a t i c p re s su re drop w a s ob ta ined by t h e use of a micromanometer connected d i r e c t l y ac ros s one i n l e t and one o u t l e t t ap . These p re s su re drops were i n good agreement wi th t h e average p re s su re -drops.

I n f i g u r e 3 a r e photographs of segment number 5 mounted i n t h e wood duct , showing t h e rounded s e c t i o n and t h e r e l a t i v e l o c a t i o n of t h e t h r e e i n l e t s t a t i c p r e s s u r e t aps .

SYMBOLS

The fo l lowing symbols a r e used i n t h i s r e p o r t :

A f ree- f low area , s q f t

D e e f f e c t i v e diameter of r e a c t o r segment, ~ A / P , f t

F f r ee - f low f a c t o r ( f ree- f low a r e a / t o t a l f r o n t a l a r e a )

( f / 2 ) ' average h a l f - f r i c t i o n f a c t o r c o r r e c t e d f o r momentum l o s s

4 ( f / 2 ) " average h a l f - f r i c t i o n f a c t o r c o r r e c t e d f o r entrance, e x i t , vena-contracta , and momentum l o s s e s

G mass v e l o c i t y (mass f l ow per u n i t c r o s s - s e c t i o n a l f r e e f l ow

a r e a ) , (t ) , m / ( s e c ) ( sq ~t )

Q a c c e l e r a t i o n due t o grav i ty , 32.2 f t / s e c 2

Kc vena-cont rac ta pressure- loss c o e f f i c i e n t

L l eng th of r e a c t o r segment, f t

P we t t ed perimeter of r eac to r segment, f t

P s t a t i c pressure , lb/sq f t

AP ' measured p re s su re drop co r rec t ed f o r momentum l o s s , lb / sq f t

Ap" measured p re s su re drop co r rec t ed f o r en t rance , e x i t , vena con t r ac t a , and momentum los ses , lb/sq f t

Aheas o v e r - a l l measured s t a t i c pressure drop a c r o s s r e a c t o r segment, lb / sq f t

. . . NACA RM E52105

. . A ~ e n ent rance p res su re drop, lb/sq f t . Apex e x i t p re s su re drop, lb /sq f t

AP, momentum pres su re drop, 1b/sq f t

vena-contracta pressure drop, %/sq f t

\ R gas cons tant f o r a i r , 53.35 f t - l b / ( l b ) ( O ~ )

R e Reynolds number, D,G/~

t s t a t i c temperature at entrance of t e s t s e c t i o n ( i n l e t - a i r tempera ture) , OR

At s t a t i c temperature d i f fe rence between ent rance and e x i t of t e s t s e c t i o n ( taken as zero f o r t h e s e t e s t s ) , OR

V ve loc i ty , f t / s ec

W air flow, lb/sec

a# A P / P ~

P ~ t / t l

)I absolu te v i s c o s i t y of a i r , lb/sec - f t

P air dens i ty , lb/cu f t

to shear ing s t r e s s defined a s average f r i c t i o n f o r c e p e r u n i t a r e a

Subscr ip ts

The fo l lowing diagra-tic sketch of t h e t e s t s e c t i o n d e f i n e s t h e s u b s c r i p t s p e r t a i n i n g t o t h e var ious s t a t i o n s

a i r f l o w

NACA RM E52105

#

RESULTS AND DISCUSSION

A l l t h e p e r t i n e n t measured and c a l c u l a t e d d a t a presented i n f i g u r e s 4 and 5 a r e t a b u l a t e d i n t a b l e s ~ ( a ) and ~ ( b ) . Values f o r en t rance l o s s and e x i t p re s su re recovery a r e not tabula ted , inasmuch as they were about t h e same o rde r of magnitude.

F r i c t i o n f a c t o r s based on measured o v e r - a l l s t a t i c p re s su re drop co r rec t ed f o r momentum l o s s . - The average h a l f - f r i c t i o n f a c t o r s ob ta ined f o r r e a c t o r segments 5 and 10 a r e shown i n f i g u r e 4, where t h e average h a l f - f r i c t i o n f a c t o r co r r ec t ed f o r momentum p res su re l o s s ( f / 2 ) ' i s p l o t t e d a g a i n s t Reynolds number D , G / ~ . The average h a l f -f r i c t i o n @

f a c t o r ( f / 2 ) ' i s based on t h e measured o v e r - a l l s t a t i c p re s su re drop co r rec t ed f o r momentum p res su re l o s s a s given i n t h e fo l lowing equat ion:

where

and

These equat ions and subsequent equat ions a r e der ived i n appendix A and a sample c a l c u l a t i o n i s shown i n appendix B. The u n i t s r e q u i r e d a r e g iven i n t h e s e c t i o n of t h e r e p o r t e n t i t l e d "Symbols".

Inc luded i n t h e f i g u r e , f o r ccnparison, i s t h e von Karman-Nikuradse l i n e ( s o l i d ) , r ep re sen t ing t h e r e l a t i o n between f r i c t i o n f a c t o r and Reynolds number f o r t u r b u l e n t f low i n smooth p ipes , t h e equat ion of which i s :

The dashed l i n e , i n t h e f i g u r e , r e p r e s e n t s t h e h a l f - f r i c t i o n f a c t o r r e l a t i o n i n t h e laminar region, t h e equat ion of which i s :

The d a t a f o r r e a c t o r segments 5 and 10 a r e not i n agreement w i th t h e r e f e r e n c e l i n e f o r t u rbu len t flow i n smooth p ipes ; t h e f r i c t i o n f a c t o r s f o r bo th r e a c t o r segments a r e h igher t han t h o s e f o r smooth p ipes . The f r i c t i o n - f a c t o r d a t a f o r each segment can, however, be w e l l r ep re sen ted

NACA RM ~52105

by a s i n g l e l i n e , t h e d a t a f a l l i n g wi th in +5 percent of a mean l i n e through t h e data f o r each r e a c t o r segment. Check p o i n t s were obta ined f o r bo th r e a c t o r segments and, a s shown i n t h e f igu re , i n d i c a t e good r e p r o d u c i b i l i t y of t h e da ta . A t t h e h ighes t Reynolds number obta ined (about 70,000), t h e f r i c t i o n f a c t o r s f o r segments 5 and 10 a r e h ighe r by about 44 and l l 0 percent , r e spec t ive ly , t h a n t h o s e g iven by t h e von Karman-Nikuradse l i n e f o r smooth p ipes .

F r i c t i o n f a c t o r s based on co r rec t ed p re s su re drops. - The average h a l f - f r i c t i o n f a c t o r s f o r r e a c t o r segments 5 and 10 are presented i n m

I+ (D

f i g u r e 5 wi th t h e same coord ina tes a s used i n f i g u r e 4. I n t h i s case , cu however, t h e average h a l f - f r i c t i o n f a c t o r s (f/2)11 a r e based on measured o v e r - a l l s t a t i c p re s su re drops which were co r r ec t ed f o r entrance, vena- con t r ac t a , momentum, and e x i t p ressure l o s s e s as g iven i n t h e fo l lowing equat ions :

Ap" 1

(f/2)" = 8m pv2,2g

where

and

No p re s su re - lo s s c o r r e c t i o n was app l i ed f o r v e l o c i t y p r o f i l e development. Both r e a c t o r segments had an L / D ~ of approximately 14, which might be t o o s h o r t a length t o cause a f u l l p r o f i l e development. Rather t han assume a f u l l o r some p a r t i a l l y developed p r o f i l e , t h i s c o r r e c t i o n w a s not included i n t h e ca l cu la t ions .

For t h e data r epor t ed here in , the use of t h e i n l e t a i r d e n s i t y i n p l ace of a i r average d e n s i t y introduced no s i g n i f i c a n t e r r o r . I n c a s e s where t h e r e would b e h e a t add i t i on i n t h e r e a c t o r segment o r longer s e c t i o n s of g r e a t e r p re s su re drop, t he c a l c u l a t i o n s should be based on an average o r some weighted a i r densi ty .

NACA RM E52105

A s i n f i g u r e 4, the f r i c t i o n f a c t o r s f o r both segments 5 and 10 f a l l above t h e reference l i n e . The correc t ions applied, however, tend t o cause the d a t a f o r both r e a c t o r segments t o approach t h e reference l i n e . I n t h i s case, t h e data f o r segments 5 and 10 a r e higher by about 26 and 95 percent than those given by t h e von Karman-Nikuradse l i n e at a Reynolds number of about 70,000.

Although t h e f r i c t i o n f a c t o r s a re somewhat higher than t h e reference l i n e , t h e slope of t h e da ta f o r both segments i s e s s e n t i a l l y t h a t of t h e reference l i n e a t Reynolds numbers below 10,000; a t Reynolds numbers g rea te r than 10,000, the slope becomes appreciably l e s s than t h a t f o r t h e smooth-pipe l i n e .

The r e s u l t s of t e s t s t o obtain air-pressure-drop d a t a with no heat addi t ion on two reac to r segments of a proposed a i r c r a f t a i r -cooled r e a c t o r can be summarized a s follows:

1. The measured average h a l f - f r i c t i o n f a c t o r s (correc ted only f o r momentum) obtained f o r each r e a c t o r segment can be well represented by a s i n g l e l i n e throughout t h e range of Reynolds numbers inves t igated . However, t h e l i n e s a r e not i n agreement i n magnitude o r s lope wi th t h e von Karman-Nikuradse reference line representing turbulent flow i n smooth pipes . The slopes of t h e l i n e s through t h e da ta a r e e s s e n t i a l l y t h e same a s t h e reference l i n e at Reynolds numbers below 10,000, but become con- s ide rab ly l e s s a t the higher Reynolds numbers. The f r i c t i o n f a c t o r s f o r segments 5 and 10 a re higher than the reference l i n e by about 44 and U 0 percent , respectively, a t a Reynolds number of about 70,000.

2. Correct ion of t h e measured pressure drop far momentum, entrance, e x i t , and vena-contracts losses tends t o b r i n g the f r i c t i o n f a c t o r f o r both segments nearer t o the reference l i n e . However, t h e s lope of the l i n e s at t h e higher Reynolds numbers is s t i l l appreciably l e s s than t h a t f o r t h e smooth-pipe l i n e . The corrected f r i c t i o n f a c t o r s f o r segments 5 and 10 a r e higher than t h e reference l i n e by about 26 and 95 percent, respect ively , a t a Reynolds number of about 70,000.

3. The displacement of t h e curves above t h e reference l i n e would i n d i c a t e t h a t some re-evaluation of the e f f e c t i v e diameter, or inc lus ion of o the r parameters pe r t inen t t o t h e geometry of t h e segment would be required f o r cor re la t ion of t h e da ta f o r both segments.

Lewis F l i g h t Propulsion Laboratory National Advisory Committee f o r Aeronautics

Cleveland, Ohio, August 24, 1952

a*. .- NACA RM E52105

APPENDIX A - DERIVATION OF THE PRESSURE DROP EQUATIONS

A schematic diagrain of the test sec t ion showing t he various s t a t i ons i s given below:

a i r flow d

I I

The f r i c t i o n fac to r can be defined by t he following general equation:

where TO is t he shearing s t r e s s defined as t he average f r i c t i o n fo rce per u n i t area.

Equation (1) can a l so be wri t ten as:

Ap " Ap" ( f /2)" = a

8 L/D, p ~ 2 / 2 g 8 L/D, ~ ~ / 2 ~ ~

The following equation defines the Ap" of equation ( 2 )

The f r i c t i o n f ac to r a s calculated by equations (2 ) and ( 3 ) does not represent t h e exact value of t he r a t i o of t he shearing stress at t h e w a l l t o t h e dynamic pressure of t he stream, inasmuch a s no pressure-loss correct ion was applied t o equation ( 3 ) t o account f o r ve loc i ty p r o f i l e development. The reac to r segments t e s ted had an L/D, of approximately 1 4 , which were f e l t t o be too shor t a length f o r full p r o f i l e development. Rather than assume a f u l l or some p a r t i a l l y developed prof i l e , t h i s cor rec t ion w a s not applied i n t he calculat ions.

The various terms of equation (3) a r e derived as follows:

Entrance pressure loss , Ape,. - Losses of mechanical energy occur

i n t h e flow stream i n the region of contract ion from s t a t i o n (1) t o ( 2 ) . The genera l energy equation between these s t a t i o n s can be wr i t t en :

Assuming no f r i c t i o n and incompressibi l i ty of the f l u i d , t h e follow- i n g r e l a t i o n s apply:

PI = P2

and

Hence,

where A ~ / A ~ i s defined as t h e free-flow f a c t o r F, and rewr i t ing equation ( 5 ) i n terms of mass veloci ty i n t h e t e s t sec t ion r e s u l t s i n :

Ex i t r ega in Apex. - The momentum change between s t a t i o n s (3) and (4 )

where an expansion occurs can be s t a t e d as follows:

Assuming incompress ib i l i ty , equation ( 7 ) can be wr i t t en as :

A s before, % / A ~ = F and A ~ / A ~ = F; the re fo re ,

. . NACA

I n o rde r t o w r i t e equat ion (9) i n terms of en t rance cond i t i ons a t s t a t i o n (1) t h e fo l lowing was assumed:

I n t h i s case t h e Ap used i n equat ion (10) i s an approximation i n t h a t t h e va lue f o r Aheas was used i n o rde r t o avoid a t r i a l - a n d - e r r o r s o l u t i o n . The e r r o r i ncu r red by t h i s assumption i s n e g l i g i b l e .

Equation ( 9 ) can be r e w r i t t e n with t h e a i d of equat ion (10) as fo l lows :

where

and

I n t h e s e p a r t i c u l a r - tes t s , wi th no h e a t add i t i on , f3 was, of course , always equa l t o zero.

T

Vena-contracta pressure l o s s Apvc. - The vena-contracta p re s su re

l o s s was taken as a f a c t o r K, times t h e v e l o c i t y head of t h e s t ream i n t h e t e s t s e c t i o n s and i s given by t h e fo l lowing equat ion:

+

where Kc i s a func t ion of on ly the f r ee - f low f a c t o r of t h e t e s t s e c t i o n . Values of K, a r e g iven i n r e f e rence 1 p l o t t e d aga ins t f r ee - f low f a c t o r .

Momentum p res su re l o s s Apm. - Using t h e gene ra l momentum equat ion and assuming p1 = P2 r e s u l t i n the fo l lowing equat ion;

. . a .

NACA RM ~52105 . . .

Rewriting equation (15) by means of equations ( l o ) , (12) and (13) gives :

I n the calcula t ions just described, t h e t o t a l and s t a t i c tempera- t u r e s were assumed t o be the s e e . Several check calcula t ions which were made a t the highest flow conditions showed t h a t t h i s assumption gave negl ig ible e r ro r . With heat addit ion and at high flow r a t e s t h i s assumption i s obviously not t o be expected t o remain va l id .

e.. NACA RM E52105

APPENDIX B - SAMFm CALCULATION - RUN NUMBER 1 FOR

R~ACTOR SEGMENT NUMBER 5

Effect ive diameter, De = 0.0208 f t

Free-flow area, A = 0.0385 f t 2

Corrected a i r flow, U = 1.712 lb/sec = 6162 lb/hr

Absolute v i scos i ty of a i r , p ( a t 506' R ) = 0.0426 lb/hr-ft

I n l e t - a i r temperature = 506' R

I n l e t - a i r pressure = 39.66 in . Hg abs. = 2804 lb/sq f t abs

Free-flow fac tor , F = 0.92

NACA RM E52105 e m em* . where Kc = 0.5 (from re fe rence 1)

REFERENCE

1. McAdams, William, H. : Heat Transmission. 2nd ed., McGraw-Hill Book Co., Inc . , ( ~ e w York and ond don), 1942, p. 122.

TABLE I - MEASURED AND CALCULATED DATA FOR REACTOR SEGMENT ISOTHERMAL PRESSURE DROP TESTS

( a ) 3ea:tor seg-.er,t nurker 5. Free-flaw area. 0.2345 sq-are fee:; f ree- f lcw f a c t o r 0.32; eqiilvale7.t diaz.eteF 3,, 2.3235 f e e t ; ler.gtP. t o dla-.eter r a t i o L/3e, 14.2.

-

1

2

3

1.712

1.673

1.644

h a l f - f r i c t i o n

f a c t o ~ (f/2)

Aeasured pr+ssure

drop AP

( lb /sq f t )

Calcula ted c o n t r a c t a pres-

s u r e drop

APvc (1b/sq f t )

xa lcula ted ms2cntun pressure

drop APm

( lb /sg f t )

I n l e t a i r pressure

(lb/sq f t abs)

v e n a - C o r r e c t e z c o r r e c t e d half-

f r i c t i o r , f a c t y a ( f / 2 )

I n l e t a l r temperature

(OR)

Run

506

516

508

4 1.515 i 5 1.493

6 1.433 7 1.299 8 1.283

9 ' 1.134

10 / 1.043

~ 1 r Ilow ( l b / s e c )

C u r r e c t e d f o r monentum, .ena c o n t r a c t a , e r t r a r c e , and e x i t _ O S S ~ S .

514

538

507

512 511

508

516

508

520 510

518

512

512 518

522

512

518 508

11

12 1 3

14

15

16 17

18

19

20 21

Reynolds number

2804

2768

2732

.868

,834 .730

.721

.689

.651

.651

.604

.590

.562

.507

I n l e t a l r Mach

number

2659

2632

2573 2514 2500

2389

2369.

2252

2267 2254

2210

2210

2213 2184

2181

2207

2156 2127

78,300

75,500

74,900

22 1 .478 23 / .420

68,500

68,000

65,400 58,900 58,303

51,730

47,100

39,500

37,400

33,300

32,400

31,200

29,500 29,300

27,000

26,700

25,200 23,100

14.8 I 11.7 7.85

8.11 5.67 4.89

4.78

3.93 3.43

3.05

2.91

2.29 2.00 2.00 1.04

.749

.653

512 / 2176 ' 2 1 , 7 J O ! . I 4 1

518 2120 1 1 8 , 9 0 0 .I28 24

25 26 27

28 29

30

31

32

33 34 35 36

37

38

0.339

.386

.384

.344

.344

.288

.263

.255

.234

.224

.203

.202

.I82

. I62

.162

.I11

.093

.080

147

144

140

.366

.362

.355

.331

.328

.303

.283

.246 ,

.237

.237

.210

.200

.I88

. I92

.I79

. I71

.I68 5 2

:corrected f o r

512

526 517 523

524 522 514

524

522

518 522 524 524

524

524

119

117

110 92.1 88.4

73.2

63.0

44.5

42.5 31.7

32.2

28.7

26.0 26.3

23.5

21.5

19 .3 16 .5

momentum l o s s .

2148

2116 2095 2091

2090 2089 2132

2082

2084

2081 2079 2081 2076

2074

2074

15,600 1 . l o 3

15,300 13,000 11,700

11,400 10,400 10,100

3.100

9,000

8,200

7,300 7.200 4.900

4,100

3,600

. l o 3

.089

.081

.079

.072

.067

.063

.063

.056

.050

.050

.035

.029

.025

- Run

TABLE I - Concluded. MEASURED AND CALCULATED DATA FOR REACTOR SEGMENT ISOTHERMAL PRESSURE DROP TESTS Zi' (b) Reactor segment number 10. Free-flow area, 0.0386 square feet; free flow factor, 0.90;

equivalent diameter De, 0.0201 feet; length to diameter ratio L/D,, 14.45.

Air flow (lb/sec)

(lb/sq ft abs)

a Corrected for momentum loss.

- - - - - - -

Reynolds Inlet air n3mber Mach

nuntber

Measured pressure drop AP

lb/sq ft)

Calculated mome n turn pxssure drop APm

f lb/sq f t

Calculated vena contracta pres-

sure drop APvc

( lb/sq f t

Corrected for momentum, vena contracta, entrants, and exit losses.

(a) Number 5 reactor segment.

Figure 1. - Photographs of reactor-segment mockups.

(b) Number 10 reactor segment.

Figure 1. - Concluded. Photographs of reactor-segment mockups.

Air supply

r Pressure Filter, / regulating

vn1 vr

'-+--I r Valve

/ / Wood duct

Flat plate Inlet tank rice \

( a ) General piping layout. Thermocouple Test Measured t static - - - pressure

(b) Installation and ins trunentation of reactor sement.

piare 2 - - Schematic diagram of experimental setup.

section

Figure 3. - Photograph showing instal lat ion of number 5 reactor segment, rounded entrance, and location of pressure taps.

Number "10 ( t a i l e d symbols i n d i c a t e

F igu re 4 . - Average h a l f - f r i c t i o n f a c t o r ( f / 2 ) ' p l o t t e d a g a i n s t Reynolds number f o r r e a c t o r se-ents numbers 5 and 10. Fr ic t , ion f a c t o r c o r r e c t e d f o r momeritum l o s s .

0 Number 5 0 Number 1 0

( t a i l e d , symbols i n d i c a t e check p o i n t s ) -- --- Laminar f l ow

Von Karman-Nikarad.se

hLl cd k Q,

4

/ *001400 GOO 900 1000

1 2 000 4000 6000 10,000 20,000

-557 40,000 60,000 100,000 200,000

DeG Reynolds number, - CI

Figu re 5 . - Average h a l f - f r i c t i o n f a c t o r ( f / 2 ) l t p l o t t e d a g a i n s t Reynglds number f o r r e a c t o r segment numbers 5 and 10. F r i c t i o n f a c t o r c o r r e c t e d f o r momentum, vena c o n t r a c t a , en t r ance , and e x i t l o s s e s .