Study of Jet-Propulsion System Comprising Blower, Burner, and Nozzle

NACA ACR No . E4E06 APPENDIX A TERTST H03SEPOWER OF J'ET In th8 follovling analysis} terms bav ing a negligible effect on the result "Were omitted from the equations.

The thrust horsepm'ler of the j et - propulsion device is given by applicat i on of the familiar mom e ntvm e~uation (1) It is expedient in the analysis to malm use of a fictitious jet veloci ty defined as follovls: Let V5a be the jet ve2.oci ty for the case where no fuel is burned in the c omIms tion chmnber but ' where the blower pO\ver} mass flo",} pressure at the combustion - chamber entrance} and the diffuser and b10,,:er efficie:a.cies r ema in the same as fo r the case 17here fuel is burned. This condition is mechanically achieved by adjusting the disch arge - nozzle opening.

It is further reql : ired in the definition of V5a that h ea t gene r- ated by turbulence resulting from energy losses in the diffuser} the blm-rer} and the burner is removed from the gas as it is fonned and therefore does not contribute to the exit velocity V5a' Let a, be defined by the relation ( 2) Then 550 thp (3 )

lw

2 0 When the theo r etical gain i n kinetic energy of the air for the cold condition is equated to the difference bet'l"een mechan i cal power added by the blower and the power losses at the diffuser and at the constr i ction in the combust i on chamber caused by the burner} there is obta i ned HACA ACR No. E4E06 19 An 8.lJproxilllation is apparent in equa.tion (4) wbere tbe d.iffuser efficiency is assllmed. to apply to t:he cl"ange in velocity :i.'rom Va to V2 ' The complication of a more exa.ct relation is not consid.- ered. viarranted. because of the sma.llne ss ai' the error involved..

Solution for VSa/Vo from equatton (4) gives (S) whero ( 6) or and.

Tj , Lot be d.efined. by d.

(8 ) Equation (6) becomes 5S011 Pe b (9 ) X = - (1 - Tjd. t ) ~2 2 0 Part of tho d.iffusing action bakes pJ.ace in the free-air stream ahead. of the nacelle . The d.iffusel' effiCiency includes losses in thls l'eeion as '-Tell as those occurrin,~ in the diffuser proper. When the velocity at the combustion ch...anber V becomes greater than the free-air velocity V ) a nozzle rather than a o d.iffuser is required. In such cases the sign ahead of the teI'!!lS N ~ CA ACR No. E4E06 and s h ov~d be ch onged in or der t hut these terms agai n app ea r as a loss in e ner gy . In al l cases th e efficie nc ;y TJd i s defined as the r a tio of the true chance in l~in('tic energy to the ideal change in kin e tic energy for the s ' 1me entra nce concH tlon and pl' eSSl,U'e cllRnge.

Ther ef o re) c on dtti o ns w here V 2> Vo Sh OlUd b e treated as spec i al c ases where) de pe ndin g on tile ove r- all efficiency of the venturi) th e second t erm on the ric.ht-hanci side of e'luat ions ( 4), (6)) and (7) c an be eit her corrected cr om itt ed .

Combi nin g e ( 3) a nd (5 ) 'lu at i ons I

550 thp ," --- '-

-- .-

(10) ya (1 + X)

2 LC

v

~l

1MV 2 2 0 The equation for the j e t thrust per unit mass flow is The qu a ntity . a, may be dertved in the follov in g manner. The dischar ge ve locity of the j et is given by the o'lu ation

1-- - ---· ---

V5 "C ) 2 Jc T [ -1 _ (P o \)7- '

V V P 4 L ,P4

wh e re T4 an d P4 are the totnl temper nture an d preSSlITe) r es pec - tiv el y.

For the cold con dit i on a similar e xpreseion fo r V 5a may be o bt ai ned with T4 replaced by T2 a ' where T2a i s a theoretical tot al t emperature at the burner entrance correspondin g to the case vlhere the jet dis charge vel ocit i s V5a· The va::" L lC of T2a J o bt a in ed. f r oLl the con ditions given in the definition of V5a is el l}) otnI' _t io..ll;y- NACA ACR No. E4E06 (12) The rema rk that fo llow s equation (4) applies also in the case of equation (12).

The j e t ve l o cit y fo r the cold conditi on is then g iv en by (1 3) Then Wh en the first tw o terms of the series expans i on for the

-r.:1

tlP 3 -4\ )' t e :nn taken are

- --p;)

~ I

V5 = C

v

--- ------ . ------ tlP3-4 T4 P3T 3 JC T p 2a

J

NACA AC... No , t:4.H.:06 1r111cre the assumpc; . on is made that. T2a/T3 may be taken equal to unity i n the term containin g 6P3-4· '1'hen (14) V 5 == Ve' a w hE- r e y- 1 C

(Po \ -y-

y ~ ~3-4 (1 5) 2 - _ ,

( 1 - - .- - ' --

-

\ )) •• I 2 • -0/ P3 V5 a Thus (16) But ~P 3-4 If t he a1?proximations are made that V4/V3 - T /'r2 a and Y3 = V2 , then When Y Sa is elimlna ted from tlJe e-luation for ( by mea.1S of equa- tion ( 5 ), there r esult s -- - -- - --~-- -- ~-~--- ----- -- NACA ACR ' ~o . E4E06 ?'-=.~, p '\ )' ( For the tliJe of s;:-s1.em under d i sC USSivD , the term ~) \P3, equation for ( ma;{ be r eplcced by unity without introducing a]!preci8.ble error in t:~e .:'ra ~ ,til,.,a 1 ra:.ll:,e of ope Tat J. (·n . 'i'l:us Com'binati :m 0_ . 0<luaU. ons (10) alto. (15) g . Lves the tYJrust YJorsepowe r equation as

r- - ----;-· - · -- l

S50 th:, { C 2 t 4 (l X)

- 1 I (1 8)

\1 V \' I

1 2 , T I 2a 2=MVC.

J Equat i ons ( 11 ) and (16) give the ti1rust equation as I - ---- - -- - _._-

/ V 2 T4 (2 2 \

(19)

F /}II = C ( ;;-- V 0 + VoX) - V 0

v

12a / The ra tio of tll? %P Can be oerived from eq uatjons ( 6) e and (18) or f:;:om equations ( 9) and (18) 24 NACA ACR NO. E4E06 i : I

~J ~cv~,~::_~

thp ( 20 )

x + 1 - Tld 1

In this analysis the thrust obtalned. from the rearward motj . on of tl1e fuel vTaS neglected . The follovTing relation vT ilJ. correct for this contribution to the tl1rl.lst : WfJ' \ W.V 210 - ( C orrected thrust horseIlO\' ler = thp 1 + + ....f.J~. __ ._ 360Cn,1 ) 1 . VOl, b / The thrust of the enGine exhaust vms also neGlected.

NACA ACR No. E4E06 25 APPEr-JDIX B FUEL COnSmfPTION Combustion of the jet fuel occurs at substantially constant pressur e j therefore or The term Mcp (T2 - T28,) 3600 represents the heat Bene~ated by turbulence :L n the diffuser and at the blol-rer. This heat i s usu- ally small compared with the l1eal; generated by combustion and in most cases can bo ne gl e cte d . I t will be neglected in the subse- quent equat10ns . For lov[ effj ci e ncies, to correct for this approximati on) it is merely llecessary to subtract from t he f uel rate obtain ed from the ensuinG equations a value equivalent to the heat generated by tu:cbulence . Then from equation (1 8 ) ( T4 c

3600 T2a .--- 1 ~ 550

p \,T2a TlcW fj = J . ---- (21) (lb)/(thp-hr) ., thp'

I

I 2 T4

hV 2

(1 + X) .. 11

\( C v £ I T2a J L If c 7.728 ( Btu)/(slug)(OF ) p and h 1 9 )000 ( Btu)/(lb f u el )

(T4 _ 1)

805 . 3 T2a \T / TlcW fj 2a (lb)/(th:. )-h1') thp = T4

1 --

V 2

(1 + X) -

_ yc/ '

I T2a

J

2G ~ffiCA ACR No. E4E06 The engi -::1 e fuel consumption can be assumed to be proportional to the eD g ine bra ce bo rse )m.re:(' . '1'11118) 'df s == BP ( lb )/ (hr) (22 ) e F ro m e q,u at':ons ( 18 ) and (22) Vl TIP 550 c J f e -- . ::.. -- x - .. ::- - --- .. --- .:.._- -.-_.- '- .. .- (lb) / ( t: Jp- ll r) thp (2 3 )

~N 0 J r' -;- .-- T : ~ ----- : ' I

2 I !I J C V E: - - ( 1 + •• ) 1 I I \; T2D.

...J From e q,ua tion ( 9) , El q,ua tloll ( 23 ) b ec o mGs - ----- · -- -- r· - ~ --- .- . .- == t tl }?

As suming .,.., ' 0. 90 " e and B 0. 6 ( l b f'uel )/(b bT)<lr) then (2 5) (lb)/(tl1 ~ -hr )

- _. - -- - - -- . - .~ -- NACA ACR No. E4E06 27 APPENDIX C RELATIONS BE'l11EEJ.~ ATMOSPIlERIC CONDITIONS AND CONDI'l 'IOlm AT COMBUS'l'IOH -C HAMBER EWi'RA1~CE Accllrate values of V and T2 may be found by the followine metho ,d . The conditions after the diffuser and. before th e blO'loTer (V J D , an d. Tl ) can be 0 b La incd from the follm.,ring three formulas: l l From the conservation of ener g;y

k

J 2 .

+ T (26)

JC 1

From the definition of diffuser e.(ftciency

, L-l

'1

/ ) 'l

'r f ~l

:= T)d (T - '1'0) (27)

l o 1 \--

- 1 J

I Pol L and MRTl Vl (28 ) A "9 D 1 The valu es or' V ) '9 2) and T2 may b e found by the follo w lng fOI'mul as:

Z.:l

, ,, )' (2 9)

(~~)

\P

J . I (3 0) and I

I

J

-~- " - -_.

NACA AC IJ. ·, No . E4EOG

(31)

'TI For a n a ppr o::-: i 11lb te va .J.l'e of V , values fOl' and P?

-'-2 ....

j.n can be l 'e ple,cso . T ancl equation (31 ) . Equations ( 26 ) b Y' Po a 110_ ('~O ) g j.ve 1 2

l-v 2

'J 50P e

-:zy 0

2 2 -_.+ (32) 'I'

T9 ;- ~~Jc- =

Jc+ 2

JC p p P waich c an then be use~ to fied T .

If M, P T O J lJ 8:1.0. Vo a1'e blown 8!ld V2 is a dRumed eJ OJ to l'e equal t o V as an a p.Y.' 0x i: ,' at-':'oa, t"Ol1 .l·or any va~ne 0 ... ' V l l the values of Tl an,l T2 calJ. be aota '.De ::' f : .'om equa t' ions (26) and (30), re2'!. ~ ec.tiyel: '· . By u:..:'<) at -th::'s u.:e G:(_~ (J th e valn (; s of PI and. P2 can be obtaille ct from 0q.uat. i 0ns (27) O,Ld (29), r es!lectively , and the v alue of AD from equation ( 31) .

1. P i nk el , Benjamin , Tur :'-t.~: , L. Richard, and Vo es, Fl'erl ; Des ':' gn of N , zz :;' es f a .:. ' t :le In r Lv: . J.ual C: r linder Exhaust Jet Propulsion Syst om. NACA .A 8H, A" ) l'il L 9 4~, 2 . Die hl , Ha1..ter S . : Standa:r 'c< Atmos-pllere - Ta bles a nd Dat a .

N~CA Rep. No . 21 8, 1825 .

--~ ---- -n += en 10 ;0 :z: o fT1 fT1 o :z: > n > > n

-

--------~

I I I

Vs TS

s Po

-,

......J 1

v

C

------------ AERONAUTICS

ADVISORY

Nozzle

FOR

AP3-5

-2

NATIONAL

£-,( I I

I

pt

~

COMMITTEE

~I

chamber

~P3-4

T]c

Combustion

3 I 1<

p >1...

system.

H Q) C H ~

~P2- I I

2 T2 P2 q2 P2

V

p

jet-propulsion

H Q) ~ o rl !:Q 'Ylb

of

1 Pl

VI Tl

lid

DIagram

-

Diffuser

,/

-

1.

-

Figure

Vo To Po

o ,

NACA ACR No. E~E06

Flg.2a,b x , .9 1.0 2 345 6 7 8

0 1 . 2 . 3 . . 5 . 6 7 . 8

- . 1 .

.. ,.

, 'I ; ,.

_.

.. . ~ r- .j. , ..

' - ~ -k ~+ +- l·

NATIONAL ADVISORY . , .

.. - .I--- t- COMM I TTEE FOR AER ON AUT ICS -· f+',H ---+ -+-:: . 1- "" -.l ,, . +-+-H---+.,.--J- ·· -+- , ·+---,+-+-1- -+'· A-+ -'J fk 7 IY ... _. _ + __.. _ _. . ... _ + .; .I---1--+-+,+--,-l __ +-.;.:. : -+ . -,-l f'-"'-j.2-I --+-I-"-+--+ ' ' ''-. . +-0-: ' -1'--'-11-'4--' '''''''''' / -+ V .. ... " .. . .. )' -y 5H-+-I-4-+-~-+-I-4-~~-+-I-4-+-~--+-tr~-+- -+ I -+-+-4-+-I-4-/~~~-I-~~~ 1-- - _ .. ·-- ~I-'HH 4-++ . c , ~ 4 =1-- 4-4- · +-1- ) . _ , .

. ,. J.;--- / , ,

'"

~ .<: ..,

~

2 ~

l

'" IN I ... .. , .- .. - .. L.

----- ·- 1 - f--- ~ - I T 4 I \ _.- .. J. - .. ~ . .- - . I f- - - f

- ~

t~ ! T·· I

, I I Il I ._ -

. ! .. .. -

I-T-- - -- 1- ,-- ,

-f-

I' i I

\ ~ \

-

-

j ~ \ _ ..

- -.- -. f--4-- .

-1- - I- --r-- - -- - 3 - i -

\!\

\ \' I .. _.

.. _. t- . ..

i .- .

1- -

..- +- - H-- . t-

+--

\ ,

\ t \ \ + - '1 1\

~ I~ ~~ ~ !

12 -, ~ \ ! )0.: f'."

1Il _ . \' f\.

l l ~ .J

1'; 1--'

['::: 2. 1 \ I'(

J\ 1 \ !\ 2~:J

",,",

"'~ 10 , - '1' 2

","' I"\, i "- t", "':-- t'--. t-..

f'. a f'." '"

._t\ ,0

~ - h ......

i ~

[', t...... ~ ~ r-:::: f'-. 1"'- l-:- ~ 0.

, .::: .1\ 1-=-:1:-- - .r: f'.... ,k . t:--. b- ~ .., b~

"," , 1\

"- ~ ,f', r----t--. f::::i h ; I:- ~ 1"- I'-... I'-...

,0

""

6 4

""

t-- f'>-- ~ F-j.!.t .

r---- ~ P 6 1 t.... t-- t-.

t<-:L-

l ~

P- 1- 3 1

I ~ I - "" , , :-'~ b- .c . r--: 1-- ' :-:: K l- .., i I:::: t=:-

-

4 , r-.- 2 " t-.

l- , "" I

I! 1'- . ! I- _ ._ L_.

- - - . =t~ ' F " '1 ,-'- , f- .

, I- -

I -

t- I r ....,- H I ' H 'i .. . 1-: ... t- -l- 1- - 1- .1- t-

~ ~.~

H · I

i ! I 5 6 7 -.1 0 .1 .2 .3 .5 .6 .7 .8 .9 1.0 2 3 4 8

."

X (b) Jet t h rust horsepower per blower power.

Figure 2.- Curves for obtaining jet thrust horsepower.

550., P [ 2] IIp 2 X ~ ~ - (1 - TJ ) 1 - (V IV) - ~ (V Iv ) d 2 liV 2 0 'Ia 2 0 o Fig.3a,b

MACA ACR No. E~E06

I _- I , 2 .0 1. 8 1.8 1.6 1.4 1.2 1.0 1 . 0 '" .c ., . 8 '..., .8 ...

'"' " . 6 <=" .6 NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS .4 .4

I I

. 2

.2 I I

o o (al umpt o~ t ctor ot J t po .8 . 7 .6 .5 .4 .1 o 3 4 5 6 7 8 -.1 0 .1 .2 .3 .4 .5 .6 .7 .8 .9 1.0 2 X (b) Fuel c o nsumption factor of el18ine per jet thrust horsepower-h our(T)~=O.9; B=O.6 I b/bh p-hp ).

Figure 3.- Specific fuel consumption factor of jet-propulsion d evice.

X c ~ - (l""'fld' [1 - (V /V )21 _ ~ (V Iv )2 2 o ~Vo J q2 2 0

Fig. II

NACA ACR Mo. EIIE06

• Q) C) ~ .r--!

I > ~ Q) 'd ~ § .r--!

I/) r-I

S-

o ~ P- I +> Q) ...

Q) ~ Po. 0 .0 III ~ ~ P- o ~ +> +> I1l CH s:: 'T"i +> P- S ;=j 11.1 s:: I r-i Q)

e

I C) • ..-1 CH -..-I Q) P- til •

I:H 1 1 ~

Q)

-W 1, L: H~- I fr-

~ :j -I .... ~ rn: tID , ..-I o It) It) ') rr..

It) 0 0 •

• • • •

(\) r-I (\) r-I dt:{~ q ,OJ X ~££L.) dt:{~ ,It[-dq~lqt X 0ll. .zt:{-dq~/qt ,- 1I.

0:- X l"'T"'

(~

oJ A • M M Z o ~

z: :a=- n :a=- ~ n :ID :IE m ~ ", o ." '"

tel AERONAUTICS ADVISORY FOR

x

: ' NATIONAL :1 chamber.

E--<-12 COMMITTEE combustion in drop I . , I) 1 I " 5.5 •• pressure 2a- /T X (T + ) 5.0 O -owentum /V for (V f 1 - 4.5

=

2a E factor /T T 4.0 Correction 5.- 3.5 Figure 3.0

" z 0 • ~ '" 0 Ol

0) • JIo n Sa J» n ;lID '"

.a ,000 • -,-:t ..

.:·tt i : ~ ~,~ ~ L:...i ~ .L 2 ·,1·.'~ Li 'i I" r::ti: - ,,!,,,,~ 2 ~ i:: 1,000 ' j,j.j;;I; f:.:f-l :.t':i ·tit

- J, iJ'-r-F t1t

f ~ v

. . - EIEEIr;:itJ J.t!

. , r -tt!; ,~'-i= -0:1:1: . •• H' ~ 1+.'1. '+1 fffH::t-f +h,. ±l±H -l:i~R:'r.1 .

l 1-'f1 1 1 1" t ~

i I Itrll llliil

- 1' :t --+ . '. 1~ rtl ~- . ;J 4 lJ Ij.l t: ~ '."'- '-:t'":l# I-tJjT

t l::·tt:tt L~· i ' . -+- ~

P::' ft IL r-:- 1 ~ trrt' ' ~ :j::J:' r ~ IIp ~ u ,: "': ., : In

J ' :raft'

r - '·;-, H -tJ~,

'1--:i "{% -':t":t:. 14 l'r.,ill

"'" tt: ",'T, ~ tU4t : :!"f-.tl " t:.:'1b :tt_

I ~ It' h"..;: ~ I" 1,."

!

.' 'H;J 1 f ..

I 1° ,! Nit!: iir , ,1 .......

f'

u,... ,J r' ..;k .', ) - -t - " ' I ' ,:. 'hl I., " 11 +, t;:t,: ..

r" ~ In k r- h ( rI? . 1 ;j r '.

'~ :t 2 ;:,

'W

.

;~'" tt

.\;.1= t~ ti1=i: t~"""" -t!' ~J'J VI-""'" )c ~ I fr" :,:.,.l t~j: tF' : ,-- C- 'l~

r;:: r 1 I-i-....;: 1*:lt

i'"~ " · H 't',1= " :-.:r,:r:t ~t':;1' ILi;i

-t+ .... ~T-I+...r ¥rBc;t -v

" j-!- 'J', .. ·~t· ..

t...,- fit )" [1 1 ' d ;T. 'J' ·", it' 2 ''' i f ., I ~i"'fL r ~ J·'.;: : ' · 't, . c' ~r-~" ,.

.~. ~ . j"4 -~

~. r -h-. fifl-~'{-i th; ~ p- tlO,'I, 'M :"

;Ior"" ' ~ -+j rm +;-::t ~ .j.' t~:g .Eta ~4. L 1+,-+ ~ 800,000 I _ ' .!'

I '

~ #

ci,o. :,.... ", " :+ .J;, .:tz.: ~ t, i.w:' u: t,~ t" nil il ~ ~ th ;;.... T ""-- ~ . ,..-- 'Ff -'ft':-HI Hrl 1 .

J: •• '+ "', iF ?/?

.'~.

" ::;:j. ,:

· -r"

'::j.; f.';·iJl + '.

'-- L"; j, ~ ~~: e',:l: _t- "'f'

~ 0 -::1:l· +t" '1- :IjI J{" tH: -Itt S H f:.jj: F-.;.h,B:tt vct

- (l~d)(Vo ,· ~ i ~ ."!- - 1.~1..1f~t t( -otT ~~ j<:!.

"'-' I,j ii, t~.f~· H i.

T., ' _ t:J, if' --- :..;.-- oi-" ~ ;- " '''''T'" l~ . .

I· -: 7 = 8: I -: .,-j

...... ~7 If it :a :!1

' ::g ,.- ~ tr r:I r.:o ib:' ±i: .

.- ' 1 i") ~, ';-J t,'j I

y' +-':.:, j-1±t1:'tt $ Y'1 t.;..1-"

I . ~ 1 ....-- tttt: ,.- ~

e " . ') h ". _ ~ J,. ,' , --- 'IHH '1TI-f1 q I:

- " -l~

," ~ ~.8i- Irt-. 'OJ I'lr j" ~'

~ 4 J m·

J1" 1':'

t •. , M " ' .-:' D ~ :f :t t..- , f,T~ 'j TI t£~ l:!..

I__ rr I IfE 11l I n ;!'i,:.., l+t;i ~J

'2 ';1 '.

.

1 _~ ,', }\ 550r}bP " iJ . '~:,,+ jt ...... ~. lf!'f1! I

."". :;t',.:lli£

. I : iJ; 'Itl:tci', ;-' ' l l p \A"' ij;;; fF i ft-h+ IH+ l 1p:.;.q:n: I, • a .

," ., : t Ir'n, ;

e .tt¥Jt

. .r_ littttt";I-~; ~Vo.

+';.:..

,T>-+' u.-'" Q:tt:J:t,J:

t-i+ ;i~'· .t.'f:\ l·t1f

'r .t 'i,c 1"" ~ :b .tti

X 2" ; ' L' _ " -+ .

I ~ ,4 , 1: V .: r;. 600,000 2 .J , he' " I

r ' ;:, :1, J"I;' ...:.-r 'It F4 "l' f.t-/

V ~ i. : .t::J :x+ , Vo -' 2 .., .J.'

T 111"" i±t . V i;;!;..,.J...

i" ~ ij;p ~ '+'< :~~Tj' tttt J, rdj -- 41 4 li;+ } '. J .;+" li-:' lHt ,r, 'tX+ --d"" ,A'1'''f;' 1 . : ~ ,; l ---' 1 sec

I: ',,:, when

.~ ~ .. ,;. ~~ 1~+I; "i I ~ rtf ~ ' ill ,- I·t'r ~, ;,' ,. '1 H ~~ ,~ hj'~T / 1 ~j ~ t+t±.i:m 'lBiilJ!f~ ~ :j~ 1""'" tj im t',,~.

' ~1!-1 2 i on.

' T1 H ,,.\.., ~ ii: _ u .'

~ --, , 1 -'I tj.'; ,. t ~ LL,c. "'1+ It-l- j ~- ' ""'I,J{·, J ' lU'-r 1"t ' i ~.w ~"" tted . ; ...... ' I i:l _ t It ~ p-j-' ,6,. h· t'j\ i j~ ll w

-r- 8n ;W t t! .. ffi tIt: fD :;cL\J:-IL.r

,[int;tr.

~. .,-r;- n X, .L

.:til, ::;:: .:q::"LJ

f-' " operat om ,'" j;j;" 2

~4 :t;i:.-r!lt

~ ,"~j~lt:' dil ;l-FI ~,* J!" .Ji.: ili .tI:H ~1-f'f"" r tlo!otI L I;: lBtr.'[ C) '~ =..::r .

I 'it I I, j V ,i " .. itt :,-,,1 HI, '1 T i :i:;J: '~ il'T

;ti Tr·~ rho' be

lil: I tt1

ti- ~ j ott -~ 1Wt. ,:1r ;' " - ...~" .i;

r: , '-+,1 [m p !:t-!:tH tj-, D.~~'

~'" ftt tt:P;-ttl:t;:;: t!"

i 400,000 r~.L' .f]: ~ 'It f f L

f" '--, ,;t±:I#f:~: $'i rr ould

•. 1 r'-' t i-!""' ) 1 take l ~~+-~~--~J--L~ sh !Tt .

· ~ ;11-L)'I "tt li~ft' H-':t 'l:tj:j~:t:, H+~i' L~l #!+ trn.

lli

dllii

~ )

'1l:j:f+.f+t':#l!

· .•

A';'

:±:.

-.-;- ' 1-,: I'l., r , 1"LiJ~ !;-rt tor 2

... 4' tlj li~i tiL

+ _ ~

t' n'!' I: r

1 ' ',1 ';~

.-itl I CI;.' ~ ,u:tt:l-tt :'{nl

m:rF if-T i';:m: I -v

~ ~~ -' ."

(;I 2 , ' 'l V. 1 0 t',"f' "r:r;.- ~ ~Ifil:~ - ' !I n v facto j " 'J~'1: ':1+' :"}l: t- " n" M1".- Iff ''#+;'1 tn '1' l :

YJ]

· -'

''

t~ .:.

W

+ ' : m ..... lif rl- '-~t

''-'-' #+ (1~d)(V

I ~ 200,000 ~ i'j~ +,~~.:;c i" Fr :j.

l:;:.:i:I ~tr!

Jet-thrust Term

-!:I1m

!

6.- F~e o ltmt!tltIw.#H

IJ

~~~P.~~~~-+-M~~~-4~~~

o

~ 2 1500 1""" ..

() GI 1/1 p Iir.

1 r1

"'- ~ ~ Fig. 7

NACA ACR No. E~E06

- - - - - ' P4 r 'n, !,\lI 1 00 l ~ ~ ' :;:. ,- P.;-: 8- f I "'- - "'J - - ./ .

~ ~

-

- ~i'" p tf2co

- ~

-:::::: '/

....-

1- ~ ~ -- .....

. / k::: I

~ ::;:;-

~

1/1 ~ ~ /" ~ Po ~ P =:;:; h - ~ ~ - I ..

~t- b;:::= >CJ ~ l.u ~

f l-

~ f- 8. .a lit, L k::::: ~el pP ~~ f-

.- ~ - 31 1.0 bo. I tt

~

w

i,...-- Fo l nt ~n 1106 x U ~ V ~ 8 I ~ I ~ ~ I - ,~ - l>- 1 ~OC BI )0 S M - V I ~ r- r-

i

I I I V

.c: I' V

.., b:::::: I-

.- ,0

.......... ~2( I I V .0 I k-- L ~ r-r- .-t

--

f-

i-- ::: ~

./ - I

t::: -

-

:3 Po ..-

.c: ,., l-

.., ~ f-

;;::: f- f:;:: - " e- ~ ~ ~ I

-

~ ~

r-

I . c~ ...

l2~ ~ 10,000 f.-t-" I I

- . t-'"

I-" ~ k- . ~3 r0::- b-.

8,000

- IV

I-- I-""" ~ ~ OJ Po ~ Ie.

~

+

--

6,000 . ......

<".J ~ ~ H.~

--

~ ~

-""

f""'" ;....= "';,

r+ 1. " ~2

V

PI' --:.. ,2

"- 4,000 ;- I V NATIONAL ADVISORY I ~ -

I"

; COMMITTEE FOR AERONAUTICS .f4 ! ~ 5 8~ t:d:: , -'==- - 2,000 ,,-. ( .

--

~ 1 -

I ~ b-< _ . .

~

l -- -

- - -

-

°

0. 1 3 4 5 6 7 8 9 10. 11 12 13 14 M, 61ugs/sec Figure 7.- Jet thrust horsep o wer, speciric rue1 consumptIon, and burner entrance velocity against air r1ow, for an airplane velocity or 50.0 miles per hour f or the illustrative case (TJ = TJ = TJ = 0..9; C = 1; 6P2 3 = 0.; T4 = 2260.° F abs.; b ed V - combust io n- ch am b er diameter, 5 rt).

Z

"'" OD J:o n ~ ~ n ;:lID :z o ", ~ ", o ."

~ .~ ~ ~ '

'r --~ !p ,~ "-"4 roo H++I 20

ru

.:+1

. , ,-,"1" I ~

, : -, - - 1 J: H

-t-f ..~ ~

-tH J±!: ~t ", i~¥} 'lJ,-C' ~1 " ~- It 1 ftl~tm Ij,,': ~ !

, !...

~ i - t:++ .J . ,-' "-,' "j ; t±t i-'*H~ .b"'t, "-,- i:¢ , ++ I J.

',- "

.+ '

1t ~I:t itlt -

. : ",'1 i ;- H ,Mill tt

... -:7 jt: I ff ~-t I-(.."i+/: t' r- ,1. , , 1P~_+~ ~ .

"l:t ;r! ~,,:', t-i4- :'"J-=[ ..1'"1- :J-i:t 4# it· ~.

I ' 'I·

. :ttJ: ';t'

1lj:ffi __ dt~

: ,-, I 'ff&lffli

J., fEffi~; ... ,""\ "1+ ' t~ '±::- P,':

~,;y , ttf ri <.-1'

: Ifl;f

v

, - illustrative - , ' ~ -.-, _'-~_ , ·11: ~.: ;:t;'J ,rr~F-r-~' 1::-~ -;:.i.r~

~~ , ±:!l:'l~ =.w I I;II~ f& m-,-j-

I

- .4-m t:tt:tt""; : ttl.

"1 ,

~" 1' 'j: ~

-- \ l , ', J.1 -'j~~t">-"':rt-' _~._

1-',,!,,1 ,- l ;:r~ J ~ l+iJ

~ .W' 8': the

t , 5

, '

F d~ ~~ 16 '';' ' t---~' --:;:.: ---'-:.,.

-1i1 '-- ' , ~ I:I+i= Wf rH -1i+:- r j .

-'-i' -t lr:;-: -1m.:!

t l£ttt 1 IW I-l-; n I ~ f-

~k J: .L

: 1 j ,; ·l -I ,I tor

*-",_·jl,!j""I~' t· , .. .L.. -"- ~ 'fI-

k~R l:

,,-j-f-:.: ,'1 !

H-!:;', ,J:!-tt I,. .t-<

~ F- A ~f1Jli1 11 till I fl- I

P 1

.j-

ADViSORY :,1; t '-', -'it- ::ttj: itt .ttt:

- - ',1, :..0.- ' ;~ r;"

+" 'i~' ,:t§: +;~'" J.. ttl t;::-+,

~ ie, i11

1, jet

' • :; -r':~ j:i: -w* _ltI ~,- .. :!tt , ' .'+ (l h_, ttt~ ~ i-<:r:l: ,"'!+ l:b f'iJ- jLC -rl_'1.1-' t'~ il '-r

' [ l ~ l I WJ l r' fr. lf

diameter.

:t 'I, " ~1: 14 1n clZ'-,7 " l± ,'" .

~.

:j:ti -!

',{{ ~ t;..:;: i11+ ,,- L' ~di +-I+' t> 4j:

1 ll rtt!:1 ' tt:t f : ±-it +tct -rr~'Th

: ' _4-I, 1- :-

"

~ ~ C q t" " " ;, (J' . ~i-t 4.:_:

) d -f:H:lttlt ]'}t't1= ~ NATIONAL

ti 11,- 1-::1 ., - ~

,I

_, 1 ~ ,tl .: ~'T .....:.~~ ~-[ ~, g ..

1:f_

~ ~l~' fj:.i* ~ ' j::~

- +" 1+:=t% -tr"r/ fflt

r--:: U r h I p:t r I+l=l+ I

I

t burned

1 '

I, ,_' t,1+ : 1 • ,tl

~t / i

, ... /J ~, ::t t1 - .:1- 1:I:+ I !"J i ~P l ~ ~ I1 , lL [1' -l

i

.

J ' ~.

.,-,' 4j-tr;.:t:r :t}I.'

'- ~U"~I ~ 12

~ ff~ tlti'

L~J?F'~ ..J,.....r If -~ # -. 'rM :j±tt

i ' fWtrj l

i,-j-fj tm;J· , II 'Ii.ti "H!:I+ fuel ~, ti--::;Jc' +. ~: r:, , ~]~ tr: l-!-, rl ~ .;~ r~-I' II' :f L H,- t'-1 ~±

.... ~ It# 1-~1 H

[f 1 ~ l i -I; !

, HI . no ~ .,.'; ..J- J ~r:l

" . .~1~11:1M

~"1 r. a-t:j: rltH I~( ~ ~~ iliil'l ~JHd~: ~l-1 H:I:I:i: t-H~i ~ -, , Pt':tt:l :

+ -, n

',"-, -' ~ .. 0.L

,,~ :' c':! j' slug/sec combustion-Chamber

'1 tt - ~1:i ~ e" rr i_i I', 'r~' !~ " •• lJ.l~i+~ -, :rib -l~L:t-r;: Jill:

i_jn~ I l1 l l fti-r II r-

'

j 1

J: ~.~ r 10

~ ~ with ~ ~ t:; u c+r- ,.:i:+ r ~ _~ t~'ff F M.

f' cT.1 ++_ t'~:,!tlt, rJ± 1;

m .j:p+

r

,t ' ri::tt 'I ;.1 _' -i: .~;c

' • '~. i~ e, '-i:1~t,t =

,'" 11 :!:II~t::+j -- '"T !+-ffli=t:i"'

- + Wo- lit

Lf P P, ri- [i% p i: 1 ~

I

.

A v

~ __ -I' ' '-,~ _.. -I-~l '+, tH.L ' l~ :=P.: i-H- C r;fb \~ .

f~ Yd' -h':: it { H

I. ~ Pd:t I I-' ~' I I+t!+ If$'

}t ~ - ' : + r t }. "; "- ), f - I + U' ;J j :r j'" ,;U ~ t;i

- 1-DtttL1" +=1 ++,: ~1'2

~ r, ~ I ii OJ

>

J

condition H t " "H

,'-,-' ~J'J:l'!" ,J..:!, '~'r'- ' ,-- ~ =

Fj-:- +;:i i.~t ,.L: Lt-_ I ~f1 ~ . :t;':j:. ' ~ 4~ ~.±- .;:q: ':' I

,., -

' It. '- I :t: - 'l~.!$: ;-j :t' ,!" ;;l .' I It!:.g;+W.~ijtjtr1-1~; ~_J .:-w. ~~-.\ Jit, -- +1-j1.

H ; ~ I I ) ji'J! 'J.

p:~, .L'c:t I L, , ,-, ; '

}<i;. ~ 1

.j:~ L, -'--, .-, J. r-E i1R '" I, l - t:tT I 1+::;: +:-tt--IJ :p'~; cruise AP2-3 .Jn:::' '.

,I,' _, ':J~ ~ _ .., ~::t TJ 1i{ , ~ . .~~:,

-1 tl tit- l tT}

~ lqt~ g:g~ jj~ lrj:' ,I'·, ~-o 6 .' in r, .+ -W

- ' > -

; ,I t ::- :-11=" t,..:~ f ~ I:: b, . d:-:-+,'4'tt:l-+~t..$1 Wi

it; 1=!1=ft#~~l1:F~ t, tm

fit 1

I H-1 ~ l h- I=I',:!+

0.9J J .

~r=r H~ ::,

.1 lL

m ~-t:

,or c+i' ..j:il

f"', r!t! :Hi4-+r ttt , i-U:':. + I- ~ R ~ = "'1 'H:tl±Lt):' Hf H I ,' t

1,1, .i - f

rl r _l

; :~tL ± ~ -~-;-l.', !F1Y c" j-,'; - :':-. ' _ _+ +"".,,, "-I._-t'-+' ~#~~~~ I rr ~ ::B.=4 ++H- ±J:i+:i-;I i=fr-;:rfmTl tl

l m

·'I'III~mR~~~'~l?Il~1111111I ~d

~m

" r' r tl-I d. I_, ,J -;' ~ J ri.

~ - H i-j, ,,' I j~T 1 ,-' ~t l ;, 1

, + =

l1~ ~ m t1 4 't ", :.\. m ~ -t ttt - ' ~I:i: :t i

I'L±;~1_ ::;' 41' Ji horsepower

-1fT ~

I l1 I ~ 1li fuiijJ

LlJ~LJ I H

mm -I-I-I-!+I+

~*

' f ± i -rii

'_'_ (~b j ' r~ -1f ', x:em" : F2. , , '

+" tJ'I

~r t':u:.:: tlFr":'l+ ;·'- '~

;t tif, i=1f

l

l

h n _ ':

·..j -

,, l:'-, :-" ... '- -.,=!-::~.

fu lit ' ~ t:i~;1',~,

l ~

,I ~ , +'

r- tt+tff !' Thrust case

;~'-t.:~~_~, ~J4 ..

~N ~ i I ... :+T1II ~ +!=

k

'

~~

it

+

i:j~ 1t:f ~: :J-:-', ii -+t- :t; -E

~

irtta1!4+lJH'-1 1

" .j: ;~ 8.- j -~~ - 1+ ~ 1 'tit cr::: 1 Itt , 1-JI } -, '~~t ~ - '

~ ~ • \

~

Figure 800 600 500 400 Po

$

HACA ACR No. E~E06 Fig. 9

7000 --T I --~! ~--~ -- +-~ -r-L-+ , ~-.----;----~----~ ~ CL ~ __ 4- __ ~~~~ ~

____ . __ . __ L_~ ~ L i _! Ups }

__ =L O .

!

- " -- ~ -- I I ! I -- -+--. ---;----- 5000~- ~--~-- ---- --~ ~- -r--~ ~~~~ ~--~~---r----'----r--~---- ~ __ ~

_J __ _

o 10 . 11 12 13 14 15 4 5 6 7 8 9 o 1 2 M, sl ug s / sec Figure 9 .- Thrust during take-o f f o p era ti on for the illustrative c ase (Maximum T4 = 1800 Pj ~b = ~d = 0.9; C = 1; AP2-3 = 0 ; v combustion-chamber diameter, 5 tt).

NACA ACR No . E~E06 Fig. 10 o ~ I±W ~ I ~ I±!:lilrl r#t ±tri- ~H llJldl*Htm~lff ~ ~ {ill rill! :11:1-:1: ~t~ ~$ ~ ;;n ~ 'ttr

o 2000 4000 6000 8000 10,000

thp Figure 10 .- Variation of specific fuel consumption with jet thrust horsepower for various combustion-chamber

temperatures and altitudes (P = 1200 hpj

T'Jb = T'J = T'Jd = 0.9; Vo = 733 .fps; C = 1; lIP2_3 = 0; c v combustion-chamber diameter, 5 ft).

z: 1> ~ o -'= f'Tl o Cf)

(") 1> 1> (") ..., ."

LD , r! , "

~

.:5:P ~ t -f ..

•.

l ~t*· 1:!::"t fl"~ I " :' .... , " tt-~ -*.. :i-~fu:J: I l ~ j : -ti :~~· "'1 ::l1d~g::i1 .!:;d I r '-" I . .• air.

l!'

=-':: • .j" F' L._ ' I f ..

£-;2/2 - of i~~ ..

:;:~ "M", ''·· -41""" l I l-.: t ~ ~ -..j i;: :t:H~I;-i , ,~~l t'" ;:,:'C.

·l-· I I r. I: :!· ~."

.. •• - tr£1 ;::: ~~-.

:

:j

·j

i/f. --

..

__

·" ,. ;..4l.l.;'L. ~ .. W t

I

! l

Y:..±l velocity • • q

1- !j

,-I,~...... ~tf .. ~l~' -';.' T': I

I

1 ••• ...

... of • 1 , ''·' • :r:: -t !"·t· rl: jr:

l I

~ ,

X:,I!

-; r

~,

:j'ii •• " ·''' i;: ': ';;1 "'1

/

I f

' J i · ..

;~; ...

--t ~ 1 .J.. r·

'::' ~~1

=

I

Bl 1

I

!'; -t

-;:~ ··'t ~,~ ~UUl.4:l

r I f I

~ -r ;if' .!r-J::rtf.-:-:t ~·.

-,,... ~

EE fps equivalent

I r ~~~~~~~~~~~~~~~~~~

, :~ ;: '''~~ - : ~

lj !"I- ±cr

•. f;t:

jJ

V, ' i;

:~

r t,' pt :.: r t- ;/-: ~+mm 14 :tf· M I

~~

WW:mfU

!

tm4 ~t;!

""': J·m

I

l

J ,' •• 1 temperature

'm

::ili -1-1, m~rf:

-:-t+- H

I l

H · i "

;fJ

-Hf-rl.;::t I _ ~'

__

'i ' '; t +

~~~~~~

l .

Adiabatic +trt rJ±lfffit.m:±l l l r.m~~~~~~~~~~r8~~~~~~mrt~~~~~~ ~ rr

... ;r~i1mm'

. .

~ :i1lf.4W 1 t!-p:~: *tr~jr:mijf illW~~rum~mllillilli~~~Ld~~~~~~~~~~~

m I ~~~.-U ij4~#t~

11.-

1lll o

o

8° 60 20~~

"' Figure rr..

o

~~1~~

~

." ...., to Z s:- o o 0) ~ z IT! 4= IT!

: ~

.- L

~ ~ .--i ;" ..

~,~ .. r-t:- ... c,., 'I' .,' i;!-:: ,.- -~. "1' ~i3- -'--!'m ~~ __ t'.:1 '-,

+ ---'- £- ~ili

I I \-i,.: 1

'-- ....

i •.

.• "

"'+ ~iL-~ :t:r:l==-~ Hi ~_ ,.~

' +i~~P1-~ .,-1. -. --,..... i:t.' d_i:t~ j'~j :]T l '1-- ... H' ,,---

S T:;:;~ ~~TI -- ~~; ~if

I ' • _

.. - . I. .. ['

-, f" ",.,.~ I i~;r- ",----r+---< - .. "j' :~:i

-::~-~~;-_~ iii ;!li 1-:......:-- rj f-·, ~.--"

~ , ~l:r I 1-' . I - L.. :Y ,. ,- '1 ...

,.

"'r'''"'l L-:L '-.l.:;. , :'; I" +_.

-4-!..I..- ':.r' .. ;.:-' rru t .;'1-- "--r---r-~ ·!I,.'-::1 :!:~~. ••••••• ;~~;=

-:-:t - ;-'--.1. ~::.!:.::- ::~ . I ... .. .....

,. 200 ", ..

;--. ....J ~, , ... . .- ...

:~.J.;- -:;-· 1--1" ..... . .• ~ "J' ,~ ,-_

h-U- --"' .. -rj~ -!"Tl: :!.- f::T t'1 ., t~~ ;<i

..• .•. .-·., -t ll 'I • ~-.

.\-. ~., :::1 1-1.

+1:+" 'fe "'r .,' TM'~:...:.l t+:r.;- !j.::!-CT -~i +:---. ,'" _,_ -:~. .. ",'. ·r:.. :L--:-:+ .;-- ,,, , .. _ t~ "1" .. ;J~ :i:~ , tI ..... , -.

.~ -.~ ,- ,- ":~,i --1"-4- ..,..

·w+ 1-..0-_ ''', :-,,: "-- ,'- ft:-: ._. ,... • ::; ·' ~'I ~~~; __ : i I'·

·......,.t -4

...... .. • ,..

.....

·t~: ,.'

~T'· ,1 '~'~'I I$'rH!.;I.rt-· ~ ,[;-'.:--:t:: !f::-::-::t: l ,I,+

-r:!..1 -;;u . ::j ;<

1 ~ ... , ..... ••• , .. • ;fWf-r~:r .... . , .. t: t"' •. .......

·• :-::-: 'r~, 1 ,,, :r." ""IG'~I' .... -+-" , ,-:r --:: :,':.' II :~~~ i::::>

'.l; -,. ~4.' '--'::.r I ..... i"' " . • j

, ... 1.,. , I -

,.

.:~ -- ,' ... .: I , ~:. '--" •• - · - .• ~ ,~:-:t:-, -r- ~"'r; I- .... •• r: , :.~: , . ,.- '1" ':

... {~;~

, - ·V ," ;

''It.;.t''., ~

;-L" ". <

-~ " . •• .,1 ... ,I ", "'L;1' .•• :\.+ .~..;. .. ;L-l-: I'CT'" :.'. "', I"~ ~L:I: 1 ••••• :-.!.H --.,... 'I:; ..

i~~

,~ h:i . ' \ , .... . j . C/?'.:7 .. ;' '.

2k ~T :;' "'. t; ......

:.r1T . ... ... :~+: 't--, ,- 'J' '" . >

;. ~' '. ....... t - -t' !r:: ""'" :::' If=-: , 1·i '-''1 ~ I ~ ' , ••.

1.I'!"

'1 " I' •••••• ", - ". ." .

~ l' .,. •• 1 -' I .+~: :':;~ "~"~ 150 "' .~; ..... .. I" "t· i-~: .... J ,.,' ," ;;1- iii:

~;I' :+

, ~ I . ...

••••••• .. ," '- ~~ I' •.. ~ ". 0 i '1 •••• ' - .

' , :~:!

- ... '" .. "[' ::, -:; :~',. " , .. ;;;; :1:: '-I ;;.: Wt; l. v. I.~r, t-<: , . .

" .110

'.' ',·, ' .. ',- 1- ,F

',' ..• , •.

I:I~ I'" ,,',' ::~H .1.~I :::: ~ .' .. .:j' ••••• 'i" ;1:;

I'" ':r ;i:j

~ v • : , ' ... .... e

, ,. ,. '

... .. " V ' .. •. :.

.,. " ;; ,I~ " .... P -r' u~·~ •• 'r; - .. 1~: .".,~, ··:.A ' ... '1' !-.: .~ :... " ....

:1" : I ~

V I . J l/f

P · , ; ;"; ., " !' ,."., ....

.' t· :+ " .Y ; ... 1 .. :: .....

:~~~ , I ... :1~: ' .1 r·:'; .:: ./ ._, '11' :!:' ' .,:1 .," , ; i'!: ~.~. :';.1 .....

I• I"""" ~

·1 ..... I ' MJc

:';'~ ~. •• , ' 1 1 ,'

-. !, . ~ .; . 550r)b

...

i '-':: "-' .,. 'I' .: P:ii · L-- .. · 'I~: :1 '1, . .1:' :Ll .. '1' • ...... , :;~ >-

.t-;.Tr .~' ~ I 1,.)-"'"" ~ .

• , ..... ~ " :I· ... ' '" .•. ::: ~~ './'

"" 't'l ,l.· .:;: ::~! "I ,. ,'"

~::J:1' 11 , ~_-I ~ I:': I'" ~;;; I".I-<' f! I I kr.

1,. : ~ .

, ".'

I. I, ,. •• .. ...

~ rise 1 , . ,--, 'ILH;.r~ "~ -u- ,.. • ...,,- "" , I·II.~! : .. , ' . '~ .

!~t: .:;:~ "'" ~I'~ ;,!: "j' ,., .. ;,i : , ~ ~ 1 ·1: : !.>r: .

.. " ,' t, I'

'

. .-. - ...... '" .... ," :',' "1' ·.'l'

..... :;:~ t, 1_.1 :'t: .::: .• '-r'-~ ·1', ;:.: 'i:'

n: lA" 1,~t1"" K!

I .

j ·' .- "I

:' .. ... f·'

....

V ," .. ,!~!+t: ... 'I'~ i;-:::->:- ~-,. "'I ie,.

,.. :":h ... , t·· "" j~:~' ~ .. .... :I:~ 'j' , ...... :;;: ,: I , , : r '1 " ;' ',. •.

.J'I'k.P:

'1' I q, '" ••. ' ,.~ "'1 "1'

,. :r;... :!:: ." ",. I 'I" : ,. .• 'i! Y: ,:::: ;." blower.

I !-r •• I •••• ., ~,H'f1:J;1--:":" .~.

.

'ttl'·'"t . t ',j ., 1J1·l' ·~.:111 ~!11 a!l ~~ri-.:.J. ·' ~i:, 'fl' ,t' ... I" ., ,., "J' ;;;; iii: ~'i-, "t:pi I-t,~.~. l of .

• , ' •••••• temperature r7t 1'1 :;' : - .

.......

-:(~

!TfJ;r'"t-f 'tIl' 11 ~.£.l,! ' '.'j t1~ ~:1" ,*r .1 •.•• ......... ., >

t'" ~

I r'

'~!"l~ I .... ,. j

I.·j , ' -, .. t · •• +- •• 1· -.

~~t ~ fl"~' I'ml' i~ ~W:j~i'l' , d; : .!., ::i :;:; .::,

-:'': tLr::;;: "1:1 -'-j - ~~rr;;.;-~

fJI' l I II ~....., '" j_ •... . ratio

~~; •. .~f

~;:;,: '~~-f "-- "!< !jj'J 'i' Iii' .l:~· ~ ·t 111: I. ,_ ,,:j ----,--t- Jl.i U" 1 ""L ";'1 > :::, :;1: ~ ~~' f1 1-

'

t: + ._, - · ... - . '

-1!

r I-I :i' . P

-f ~lI I' r I :';4-w:;:.rh-1::-·~ - '~h ~:' f':1 ~ir; ·' :;".J'h~:J ;:: It;~, r H ~ lliJ ·rnif-W--'f£8·· t I r- ~ I :L' "4-8=" Adiabatic .. ~ 1}' 1 I' .. ,-' <11: · :- ,..f 'iii+W:I~l :--r. t--. , '- "" :i~i 'q: ,- ~:;; :ij: -om rL::; 1 , P,--t!;.E!"Q ' ..

.. , .

i7.1 ~i~' ....... ;': ., II~+,....

t:fTR~ :~I! ,_. - t7 --!. "1 , .," i!!-:--~'· "l' ,-1.1 :1:. '1'- ... ... :;:: ::j:

ftH'J ~:-tj.H-r~r

~~F pressure ! ·tEibf' . • ' .~ 1; -~ft1' -

-I '"

:j~ .... ••••• ,

- ;'

' i- ·T·~ 11 ............... '·'1 ·r" .... 1. It'l ' 1"- .'" ::::

.;: HI! Hi

l ~ r . T I~, , •• " l": r 1 " ...

:!

, .... . •• .~' iifffi' 1- - "L' "n" j41. I'r. r- !:.: l~mr i~~!~ "I' • :1' '-, -;,...;:triP- -. 1.

_1.

l R'!: ~~

• 'L T' Total

,-.:; •. '~1-" IT. 'H ~r

rt"'!+ W IJ:-j \--11 t ~.' --I.'" ',:; :::i:i~

t~j i'H'

R1-:; rp.n.l-. ~frl-t l W

fH-.;- [

,.

' :! .• ~

.....

i- 0-1.1 • j t::-:-rr:r-i-; -.-...

H+' ;;_.; ~w : .". .1 ~:rt!t!. f.1j'-p-r~h j.ctWi1i ~tiL "1 '" ~i--j-'

..... +-'1 ---i'ffi' t!;~

I: ; J7 'T I .• .,' R.+8- I'" ..... " .

..... ;~ ~i

I ~IP •

i

, ~ •. I.:'~H" '[--,:.1 :~~~ "~' ;"., :li: "J'

~;l: l' .. ".-i-

ill- ""I" ~:-;~ 12.-

'

~ •. H·

.,-+ ·-

~,. ~1

';1"~'~ +t, }'J"

'"f" t:l~ t-!'j lw t-JjlHI"I --.'1 '~" ~~t..: H~. ..... ;";" .r:i .i:':; - "1 ' -J1~~

mI i4";::.J,;L:i ~tr;--:.:-:- 1-,-,+ H I F m w

flm ~ "

o

5·

5H

.

• 2 2.0 1 1 Figure Q.I ~ Q.) ~ 0 Q.) ~ n!

M n;I M III III (I) M Po 0 +> ..-I r-4 .0 +> 8 rl r-4 +>

0 5 Q.I

M 8 n! Q.) M ~ II) III Q.) M n! 0

+> r-4 +> r-4 .0 +> +> r-4 8