Data for design of entrance vanes from two-dimensional tests of airfoils in cascade

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Material Information

Title:
Data for design of entrance vanes from two-dimensional tests of airfoils in cascade
Series Title:
NACA WR
Alternate Title:
NACA wartime reports
Physical Description:
57 p : ill. ; 28 cm.
Language:
English
Creator:
Zimmey, Charles M
Lappi, Viola M
Langley Aeronautical Laboratory
United States -- National Advisory Committee for Aeronautics
Publisher:
Langley Memorial Aeronautical Laboratory
Place of Publication:
Langley Field, VA
Publication Date:

Subjects

Subjects / Keywords:
Aerofoils   ( lcsh )
Aerodynamics -- Research   ( lcsh )
Genre:
federal government publication   ( marcgt )
bibliography   ( marcgt )
technical report   ( marcgt )
non-fiction   ( marcgt )

Notes

Summary:
Summary: As a part of a program of the NACA directed toward increasing the efficiency of compressors and turbines, data were obtained for application to the design of entrance vanes for axial-flow compressors or turbines. A series of blower-blade sections with relatively high critical speeds have been developed for turning air efficiently from 0° to 80° starting with an axial direction. Tests were made of five NACA 65-series blower blades (modified NACA 65(216)-010 airfoils) and of four experimentally designed blower blades in a stationary cascade at low Mach numbers. The turning effectiveness and the pressure distributions of these blade sections at various angles of attack were evaluated over a range of solidities near 1. Entrance-vane design charts are presented that give a blade section and angle of attack for any desired turning angle. The blades thus obtained operate with peak-free pressure distributions. Approximate critical Mach numbers were calculated from the pressure distributions.
Bibliography:
Includes bibliographic references (p. 10).
Statement of Responsibility:
by Charles M. Zimmey and Viola M. Lappi.
General Note:
"Originally issued October 1945 as Advance Confidential Report L5G18."
General Note:
"NACA WARTIME REPORTS are reprints of papers originally issued to provide rapid distribution of advance research results to an authorized group requiring them for the war effort. They were previously held under a security status but are now unclassified. Some of these reports were not technically edited. All have been reproduced without change in order to expedite general distribution."

Record Information

Source Institution:
University of Florida
Rights Management:
All applicable rights reserved by the source institution and holding location.
Resource Identifier:
aleph - 003806576
oclc - 124083629
System ID:
AA00009391:00001


This item is only available as the following downloads:


Full Text

L'^. '{


NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS





WARTIME REPORT
ORIGINALLY ISSUED
October 1945 as
Advance Confidential Report L5G18

DATA FOR DESIGN OF ENTRANCE VANES FROM TWO-DIMENSIONAL
TESTS OF AIRFOILS IN CASCADE
By Charles M. Zimmey and Viola M. Lappi

Langley Memorial Aeronautical Laboratory
Langley Field, Va.


,- .' -:': :-
- V-- -


NACA


WASHINGTON

NACA WARTIME REPORTS are reprints of papers originally issued tu. provide rapid distribution of
advance research results to an authorized group requiring them for the war effort. They were pre-
viously held under a security status but are now unclassified. Some of these reports were no;t tech-
nically edited. All have been reproduced without change in order tL expe-nte general cWstribution.
L P18
4


ACR No. L5GlP






































Digitized by the Internet Archive
in 2011 with funding from
University of Florida, George A. Smathers Libraries with support from LYRASIS and the Sloan Foundation


http://www.archive.org/details/datafordesignofe001ang








NACA ACR 7'o. L5G18

K:ATTONAL ADVIOjF;:' CC!..i T-T7 FR-jFP AERONAUTICS


ADV'i. :' C 'TLE: -AL REPORT


DATA FOR E:.IG: F : TRACE VINES ?RC T'O-7T'iSIO:.'.L

TESTS CF 7.F -DILS IIT CA,-ADE

By Charles II. Ziney and Viola i. L. ri


SUM:KAR_


As a part of a program of the I.A directed toward
increasing the efficiency of comrpressors end turbines,
data were obtained for application to the design of
entrance vanes for axial-flow comnressors or turbines.
A series of blo-ver-blade sections with relatively high
critical speeds have been develo:- for turning air
efficiently from 00 to 800 starting with an axial direc-
tion. Tests were .made of five FACA 65-series blorver
blades (modified 6.-A 65(216)-010 airfoils) :.:.. of four
experimentally desired blower blades in a stationary
casc-ide at lo' M1ach numbers. The turning effectiveness
and the pressure distributions of these blade sections at
various arpdes of attack were evaluated over a range of
solidities near 1. Entrance-vane design charts are
presented that give a blade section and angle of attack
for *-.' desir.. turning -r_:le. The blades thus obtained
operate with peak-free pressure distributions. .Approxi-
mate critical Mach r.uibers were calculated from the
pr-essure distribution .





Previous investigations of airfoils in a cascade
(reference 1) have attempted to simulate flow conditions
throv.gh a rotor or a stator involving a pressure rise.
The present investigation has been trade to provide
information concerning the flow through entrance vanes
involving: a pr-sssure drop. A pressure rise from the
leading edge to the trailing ec--g is accompanied b. a
reduction of velocity relative to the blades, whereas a
pressure drop is accompanied by an increase in velocity
relative to the blades. The object of entrance-vane









IACA ACR No. L5G01


design i to tu rn the initial air through a rsecified
anile with a 'ninu.ilm of Is-e". Tt seems likely that
critical speeds co:: l be inc.' uce and boundar.y-la'er
losses decreased by- eli:inratng vielocity peaks; te:ts
were consequently made for two se;its of blades to
obtain a ranch of tI.rnin an*l e for a given blade section
while aintaininrl a prereure distributi:n without peaks.
The tests were made in a two-dimensional low-speed
cascade tunnel at the LanD'ley memorial l Aeronautical
Laboratory and are a part of the :ACA progra to increase
the efficiency of compressors and turbines. The purpose
of the investiFation was to develop efficient bladec
operatin. at u- s.taegger that would turn the air through
a- "les from 0 to 80 .





a acngle of attack, -the '-I::le between the initial
air ancd the ch,)rd I'.n of t he blower blade

ad design ar.sle of-, attack f blovwr blede in cascade

q local dTna:mic pressure

q1 dynaiic press ure :f initial air

q dynami c preis ure o: air behind te blades
!, + co + I cos
q ) :!macr. dynaTrlic pre ure( -

V! velocity of initial air

V. velocity of air behind t. e o adces

V vociy of air ( vector sur of V1 and V

S victor df ffre.nc`o -f velocities V1 V,


Pl in~ tal static pressure
p. ~ .tatii presur behind the b lacdi equal t
at.espheri.c prescnre


theoretical static pressure behind the blades


P2t


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iCA ACR :':. 15G18 CC I ..


Ap -r esei drop acr ss ca "e (:. p5

S solidity, ratio of cl t_

T :r-1e 1hrourt whch alr is t lr e t blades

c chord

c tz e retical d.es7 n lift c''efl l. i
free air

SG r- e r, .n te b t' e 1o
a ,Tcer I--C


tke velar'nit' .f urd t< r':.1ec L :'. tl'h ,.lade

A- O F-S EC C j

S area o f al ar

x c ord"::i:.e C dit_ lc f ,'i e 3 -.c 3

y vertical di-'





..j j. tw:-di'e sir'L 1 o -r' '-dl
described in r fer:e _c 1 :.eei :. t) E.'
variatforn of the star -e E ;-:( .. o .:: ..dil-.
This an.a:e sa." :nade ei n1 v ad. s 1n

t.le pre ert tests, the casc.d. tin-l :- .- e r -.2:il-
fied '. elimnl.i.tin;* tbe toandi~:: -l. aer -''tr-l S.C.
onr tIe a.11ls; y.wever, _all -as, .;ic; ". a3
bour.dary-layer sl oi or the l "^rr, vieco- lef. t'"'en
the to ...d o1ttyom lades ofie ;-ca thle ofl:rs..
A vertical cros3 s eti.n ot f 0 ie. apa::r,;..; .i. C.,3-
maticall y s r- i fiue 1.

Two fam il.ies C"f bl r- bldes "-e i -et r ted.
For lOW turning ans es, ti- 'C -er ; -: 'l-.er-bl.de
sections were rsed, v.2:eeas fo t':r.i- :- : eater
than C0 a series of ex;yeri'.ntslJ. ,derived ln ..or -T--les
was used. The il-4 C5--sFries blwe -blad1e sectio..s (1-.3A

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:i..-A ACE o. L5r18 ,CONFID T.T 1. 5


orifices located chord len-th ahead ofi the blades
(fi-. 1) In all test the central blae :,C;;.-* qu' .
with pressure-distribution o.ificec.

ane!t t'hrou.F'h rhich the ir F-r.s i :i:e E
the blades was measured aporo-:i.r;ately 'or- le:th
behind te blades. 1seac urmn ir .- ts re ;.ace ';_ a
cf indri c 7l yaw tu..ie provided v.itli a& ic. -...o -'e
tube was inch in cAa.:etcr T'ith to L tatic- resume
orificec at an i!n'lvioed n o T ..e a' : the
am i with respect At tsI :ir, 'he.i cth -to' ead e ual
Dpessurer, vwac found bf cslibrat-i ... ll' .;ethod
of tkinr; ma-;:'re -er ent : u:; t :'; a; vas
ad.iuL td so t;lat the- tf te b ',:'"k t.: t':3 : fi .
were con.nectec readc tio Ca r".r !E: -.S .r."l.e at '.ich
the ar" i vwa. -et .0 f .' Ln .... Y:T'.,e
mea2urifl"A device) A.n er.? : -;.r br:e
by rurVve-info the .. .' e- to. te- >.1' lad .'e









Te blade c-arati on n .CJr"


(fip'. 5(a)) i: therefore used at a bri" f'r (cte .1
the rea'i d"yr.anic pre'su :'e "C Yh 0rc Ire c tiCs
for the dliffceert "1le. blaes at vric M .. f att'ak
for eacn sclidity are svn c f es 6 t o 2 -. S
quantrit-Ty noted is the local c "2i c por:'-urc q i vided
by Qc. The acc ura1c, I the,:- re ]' :. .ire by
th(e thaic:) aousi t-- layer aLo ta> a-l and le 4:A ffio lF


anl"es. The .--nadary: i acor, ."ich ':"e a: tgi .ti. inch

thick, was due to the length o'' t' t.; O .ells a ...head "


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':o- e:c.' lad:e secti n, the :rn- 'e of cani e of
at:a.: -at (-ve press .re di tr iit Iti s wi th ut
nd.iesi.hle pea-:o ,as f-atunl. In t-e cae of t-e
;.:.~ 65-series bla es, the an-le of attack ntht ,ave
tle- ::ax^i.;.l:i turning anIe vith a riat res :c re distri-
buter1 a'' sc-e :' cbod as he iI F ccon'i tion for a
en s13 i. 'his ianrle iE l:ibeled cs der-ign ..ngle
at attack in i.-i-e: 9 tc 270. F:r t:ie ex pe-r' enlly
desl-:: l.. d sa~einon., a --a. r.1:e o f def-c: r ar"-le of attack
.s select.' -e fro:F tihe desi- able nrecsur'e aditribu'tlron
.: t e i c-, T I 1 iti> (.* fi :Se, D, I L, and 27).
Thes e c^c 0ser:ies -: biov:er-.-..sie :drctio:7s, cwith rela-
t..vel .i critical speed-, vill effac'entl7 turn air
-f1c-lwin.' in *-i axial dtr-,ct rion, froail 0D to D0.

It is -ccn r'cT:c the precsi;re 1,i. 1 ltutrions at the
lower oddities (fs. 21, ad ) that the exit
v lo cil fes! are vC-I y Il ch lr'..r thaIrn --e -ai:n ccal
elocitie s in. the to fe. -Ths c b ade 'Eotions
.are t e.ef '~e"e n-t 'eeonrC rended fo' in.r',. I3acifos r'n;
which ir;h exit ':ch .i ce s are er.c )unl.ered- The
t:.rninp enrles for val n o..f ttach,. are .he. :Wn
t.n fi-. res C to '' a'nf t tUr un.!' an1Fes nt T',-
er:ded e.Lre indc, .Ec b.- c aie ec 1 s. ith.hirn the
an;- of C3licdit.:LeS tested, t.. 3 c:a;ca:e fc bladFs rh,:ws
cl,.: :.terisi tcs of the infinite solir di" ca. .:r. ,:5 1
'ed -a f th e, "A



-t f-' low desir cu:.ers 'c,. 0.1 and 0.2 the
rc ~-n a-1 o f attach dependc 1'itle, if Uay, up1n
.olldit. fox.' tre r-an c sa ij. it;. covered !1n the present
te't.. o the I. he- r I-ca-rr red ec ti on l s c. C .4, C.8,
and 1.2 cte anI-le .' aitt'.," fr aopti:.iur o-eration is
ecsetic .: y ir:ndes :0ndet of cnl lilty fo:' t. e ranpe fro0:
0.e to 1.00 tot vith :n increase of l idi> to I.50
the. o'i:,ir.l-. oS:erat:inr .5-n le is i:crease These resultss
are e;'cctod ea:-e i Ir,: Can .f Ts o.. ic ncreasi e in
solidity 1 odce litle charge of trni rd age anl i d,
t'hre fore, the dirc o t'in .if rean flo is ea.nred oly
li rtly. or i ." cai~ers. a. inrcr ea:e f rsl1 1 ty
ilcd 'ea aes t:,e tu:'nd n ai: le .ap.n'r.i. ab. l s i':) :ci eaC ed
turnin- an-71e changes tl.e :near Zlov so as to dCee r e
tre an' a e of attack of the l.ad;es relative t t:' -1..
_.. (* thCus, i'or ite '-~ ,t-c:i;rie. r bl.ades. the ;iRc-le -f
at ac lor optimum oD rationn must be Increa:od with an
increase 0of ol.idity.


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NACA ACH --. L5G18


APPLICATION OP R:TI.,S TC I ":C-V .:TT L:STT'r


The data obtainned .re res.eted in fi'ireC .e 2
a. d ,3 in forms intended to periit t.- i 'e and
rcor pre~o uor desitineis reQ&dily to "elect ent'rn. e 'n~e -
(erterin: a-ir assmned to be ilowi nr ai. ) I '.r a
specific machine. Twoa cdtinct din l~o ecurs
are presencied. First, ir the c'.Le .' a
ar. ics (<3ZO) tahn A'C. i'-- e:ie I-l 1r ec s
car be recoarri ede 1. T:e c *i. r :. co a *e .o sm t2;c:
to be ued to obein a r'e:l-ed n1 l e wth
peak-free pre sure, di otribuin a. r
fCc'ure -. --bin irt c co'' 1 ._ a
for tu2i inf m r'lcs le*: tin in-. these K.ncle
can be obtained directly f!ro t .n atn' _e andc
DreoS1' re-distrl'dtIon cacrt' l 'e 'cat'ton of the
depsidn heart ri may e 1ius:" ted 6 a fllo s: Sdapse
it is desired. to turn -ir 1flow0 n :n axil di.-'ct.r 20
by use o f a 'row of blade!- wi.-:th .a olid.ity o' 1.35. .fer-
ence to figure 33 fho.s t- at a bloI er bledo c. .'a-re d for
a lift coefficient of 0.i5 .~ n.i ated c::i. tht it r'..ild
be opr; oated at an an e of attac.: o.f ..5.. The ai. 1c
ofi desi.nin' sruch a bslce i riven .n rferirce .
some choice i s ava lable In "i.:te ::oli t e 'sed, it
is possible to avoid cA.:'putations 1y aiij ting t.e solidlty
until figure 3 indicates th:At a .".ow'er blade; of stadrd
camber could be used.

In order to de-sin ent-,cce rI V. for tr ." air
through an le s greater t:an 00, f; ure 2 ca. be ce
Four sentrancc-vane sect ions ave been dceveil Ad 'chat., if
used at th appe ria sorlidlit- iad. an].. l e atr:acl ,
cover the turning -angle raae of 3. to .3.. 6T e lid
lines Iepresent re ions..i wich 't he. e b lad s eve ea :-
free pressure distrib1ti ..s; thi f.o ea-l, if it
desired to turn air efficiently .-n 2', it col1
d-ne either vwith a ca :ce :of :,.C.. -f()CO bc *bons
at an anrile of attack. of 32. c; s ilidly 1.4
or with a cascade of 'IACA C4-(')O .lade ec-tio,''. .t an
angle of attack of 38.10 14 a Soliit of 1.


(7,C SL <) ,_ : ;

Data have been obtained from teo rt-' e on five
NACA 65-series bl w-er-blde secti d s.. fo ur exp ri-
mentall y derived, b owver-blade se ctions and are pr esirni ted


C >_N.7li 7`_T iATI_









10 CD TIT LTIAL :...-A ACR No. 50G18


In the Ifc r of de;'i'n rharts 'or ontranc e vanes for
.....al-flow cor-ers or turbines. These desi gn
: tarts "ive blaie sejuon and aij.le of att.ck for
an desired tulnii? anjc. Tihe os.des thus obtained
o.'icrate with pfak-free presso-e d.stributions. These
t.o se:_es of blower-blde sections, with relatively
ahirn cr tical spedsr, Nwill efiicicntly turn air flowing
i an a isal dire action, from 0' to G C


Lanl-- ?.e. or al Aeroonautica1. laoretory
Ilntional Avizsory Com'-ittes f-or Aercnautics
Lanley Tiell, Va.














2. t a.. r PIe.. a.id F n.'rton
Roert r.: The chlaracter;-ic s of 78 Related Airfoil
SecVtion' ifrn _sts. in tihe ar'ible-Dar-ity rind
:ru nel. ',Li-',.- R C[To. *60, .. ....

vcn ar;an, T.i: rolprr ': ility Eff ects in %eroldy:lamics.
;Ti.r. Aer. Sci., vl1. E, no. 9, July 1941,
ni'^i /- '"--,_O ^o








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..'".A ACR No. L5G183


UORDINATYS OR NACi C6 -2 10 BLOEK BLaDE


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'i ....I
.- r









-/: t; > i .
4 -






C,
i.( o i,"L


if


'' i




I,

o '-1 |



r' r .<,







(? 7
--.::,. 0 r
~... ''





J I

- ;'"




--" ], .


n









:ACA ACR :0. T5G18


T -41 T C-- 1 AiT


[LeTrl d frnm 7 AA 3( -, 21 -
i. __ -.._ o t .._ .._
Yip5-e; sTt!J 5- t










32 1 7 C





o r i '- .



I 44. e r il





... .c-


..17
1r 4 t'-








7 o .3 5 7.1 *'
c .: 1 7

I7"5.0635 I



G 3 Z 37
3i5.(~E "

;" E, 77


10 rf- 1 c: l-c. i
r.... i- : ... r (;l' t


is









ji



11~


~-(*- -',
T --' -


8 T '. _TIA s- L


A





S~t

-1. ~









C'ACA .ACE o. L5G18


SD:I-irS ?-' VI1CA 5-F'10 3T. ..< LIAD

: liv'c. r-. -;-. 5" : 16) 9'1 0 ;J ? i"! co lined th
S- .) x : -at' or, ter in r c: ent of chor:r ]


V




.a

.42


Ili




'-I








'-. V.~
1_
7.1P -


Lcwe-r r yf. ce


-.i y"- _


* ri* 1 e


--il .--.



t


. di 0 .C6


AtmA.7 T 'l *7
.- r ...-.
, .>s ^... 1 } .. .. ... > v_ ,D ^"7.


.C :. "" 1-r.,L


x



C







io a
9.









,2 ?C.
773 >70









' ,0. ,; 2


C

1. 14


(. o



1. 71





lj F'l
10405 i1






'-4 rK ,.



52. .1
34,9 5 4
74.6 2:
79U,3
c4.-6


C
-.515
-.57C


-.4



-1. ,51

- ~ 9
-.o79
-.929

- 'a



-.190
496


1:
1.1



i16
42


C CF 7 I.:'ITAL









"ACA ACR oL. LSG13


TA'"- V

CODIIAThE "CR ::.-.-.-. 65-(12)10 B' :'I- BLADE

F[Dr-lved fr:or iACA 5(21C) -(12) 10 airfoil coiibined with
7 = C.cOEx; .tati~o _s- and odirnacs in perceSt of chord]

p, r surUxce [ Lowr surface

S I y '- x y


.971
1. :179


1.075
5.178
6.147
7.7 1 4-


10 .C40
11 .155
11.i 79
11.5 93
11.463
11.139
10.574
9.801

7. ,03

2. /2

3-7


1.126
1.683
3.013


1.C .C9
12.612


2C.13c

45.02 9
40.196

5 ;.0- '


E4.
59.
64.
60 .
74.
78o


0
-.371
-..: 5
-.3C7
-.243
-. 090C



1 .342
.594

1 .024

1.37
1.7542
1.V48


.161
.274
.E17
1.931
4.399



19.47"
24.533
29.611"
7 .7':' '
r9. 04
44. -
50.000
55.087
60.161L
C5.214
70.245
75.2 .



c-
.. ^-~ ,'


~. r '~~i::







m. -iL i-- _


c:'::o- ?AL


913 2.001
8 2.
7i6 2.5 9r-
7... 2.8 4
7 -14 2,9;2
: 2 .


S2.


I---


10O PIDE TRIAL













'2 CfTD "

EXI-Tr.I'.TALL vi,""ZJ5E'


7,tci" L t'a



7r A -


.9V












r.

















E .7




S0' /


C
&....











7 .<.1

c.7


l0


1~


31 .;



1 1
L C ,)




+i < r

. 1. 3. ija






7. 7

i- **


t \o

. o *


I*.

.7,








C *


1 :

o r
c


5.0












1 F



. J








75
CO
70


''1
1''

C













11



I~.>'


T K '
-I -i +


.1 11 ?i :!









HACA ACR "o. L12! 8


T BLE V 1

-ORDLIATS FOR NC- 6C .- (A) o BLO .LAE


i''Tpper srirf'- ce I



.C 0...
C C IV 0


4' :







G. 7
E, i 1 2


i' o7.17 -



3-4-
11. v] F


11.94 .0




1:
'.: 4 1 70






L.. r11 .2: 0O
6 7 ,I ,




L.JT rad ius; .


-~Oc~ci


-I ~...


17'
'7

1.7





<'.3



~-.i




- -


* C,

-I.


..7' '-r -TV7 '


C.. -


1.'


7.5
10


25
'O
05
40
45
i0
CO


65
,5


70
75


CO

100


C .' -- -TI L


~---


i









N.CA ACR No. I5G18


TPELE IVIII

CTI'. CA 64-() BL :: .

[Stat i-r arie orilir.atiC ir percent of chord]


T1`'r sir fce Lower surface



1I -


10
15:





40



C

7C






I.


0,75


2. '7
4.


3.0; 6






].14
1 '
1 .1!





1 1

7. 1.;1


O0





r-

.5
.C
r
Sc



C. 5
! i









ro




95
c





Cit
C;L


0
-.02
.07
35
1.14

25.80

6.10
7.13
7 .6
8.40

8.95
3.95

3.71
8.59
7.6
6.83
6. 1l
S.L(
5.14



- 1.9
-.19


l .. -..T. rT .
cc '..' ,L. yo AERO ..-.. _CS


C 1


CO1; '. -" TIAL


T rai,. 2' .74
JL B i c .4 ; v ('*/ i









ACA ACR No. L5G18 CONFI DETTITAL

TABLE IX

ORLIT'; 13 FOR HACG 64-(C)06 BLOWER BLADE

stationss and ordinates i.n percent of' chord]


'i! :-er surface


Lower surf c


1 .00
2.09
, cs A

1.19
8.0 5



10. 00
10.319


13 .84
17.5




,i. 67
i 40



17.20
17. 00
16. 3
15 .03
I7 4,0
11 19

'7. 01
4,67

.16


0
.5
7 'Vr

5.C00
7.50
10
15

20
-,-O
0-

0 H
40
45


60
65
70
75


90


'T



1 H

.27
? -27

6.50
67
10.10
7 0





1 T. 12
i. 20
1;:'.22



10.40
9.40
'.16
C .71
.10
0 .40
S1.06
-.]1


I.E. r adi Lus 0o.2








NATITTrAL ADY ISO
C' 7 I1' FOR AIERO .'TICSm


QC; *''7 MAT,-:: X


-- H----~--------


x


.5
.75
] 1.2
S2.50
5.00
7.50
30
15

2 5
20


45


50
55
60
65
70
75
80
85
90
95
100


t













S .-.L ACIA AiR ". T.51.8






t0C I. a DI 7 r


r 2tct3-;! a.d o n 7 : ) rzc>^" "* -'***r '


v_ u -_c


-1. iC


S r- L


TQ3;i:i '3J1':L ~C


LC


r-I

















~l\











3)7







1. ii1.'.


- I












-F --







: v~
1' *j






A


*~ ,i' .1


C- -- 1~


r r


.4'0

, (O




















;C





;r:


1. ( 1 1

In~;






.~" -1
Th


















1. '1.





* 1:


ii o...
1 -
i ;r

-:








:ACA ACR o. LE13


TABLE XI

APPROXIMATE CRITIAL ACII :NUihBRS BASED (ON :-;: VELOCITIES


E LACA blo er-
blade sectior Sclicdity a
t --.~-~-~-I~--.-.,---F
5-? 10 0C.83 I
65-110 1.00 2O 55'
65-110 1.50
1 65-20 .33 I
6 21 0 .00 I 4 8'
8 5--210 350
65-410 .83 7 0C3'
65-430 1.C. 7 C'
63-410 1.50 8 0,S
6,5-10 .33 11 39'
65- 10 .00 1 59'
65-813 1.50 1 5 39
65-(12)10 6 OE'
65-(321C 1.00 16 03'
65-(12)1G0 1. 5O 08'
6 --(A) 06 .',76 27
64--(A)OC I. 5, 53
34-(B)OG .0,5 29
64-(B)nG 145 48
6i-( C) 06 C2 41
S 64-(C)0 6 1.400 44
S64-(ED)OC 1.J57 61


1.5


I





tJ


ii
1
.1i


1.7


1.8

2.2
2.
2..5

5.0
3.1-
8.3


cr


0.70


.70


.67


.64




.54
.55
.54
.51
.46
.45
Very low


CC c '.::'', "" FO3E A ~:.0LA;iiTLPIC0S


CONFIDENTIAL
T


COTFIDEITTIAL


q/q,












Fig. 1


NACA ACR No. L5G18


om





00 i-0






a We ai
a E-a 4E- 4





* *o l <
0 000







St1
0 CI)








NACA ACR No. L5G18


Chord


Tangent


NACA 65-110


Chord



Tangent
NACA 65-210
Chord


3003'

Tangent
NACA 65-410
Chord


NACA 65-810


NACA 65-(12)10


NATIONAL ADVISORY
COMMITTEE FOR AERONAUTICS


Figure 2.- NACA 65-series blower-blade sections.


Fig. 2







NACA ACR No. L5G18 Fig. 3










'--Chord line
A








B -Chord line









C -Chord line









\-C-hord line
D

NATIONAL ADVISORY
COMMITTEE FOR AERONAUTICS
Figure 3.- Mean lines obtained from tests of flexible
plates in cascade.







Fig. 4 NACA ACR No. L5G18









Chord line
NACA 6--(A)06







Z Chord line
NACA 64-(B)06







------Chord line
NACA 64-(C)O6







---- Chord line
NAMA 64-(D)06
AA 6b-Do6 NATIONAL ADVISORY
COMMITTEE FOR AERONAUTICS

Figure 4.- Experimentally designed blower-blade sections.







NACA ACR No. L5G18


(a) Vector diagram defining mean velocity.


NATIONAL ADVISORY
COMMITTEE FOR AERONAUTICS


(b) Flow through a cascade of airfoils at 0o stagger.


Figure 5.- Diagrams of flow through a cascade.


Fig. 5a.b










NACA ACR No. L5G18


o Convex surface
+ Concave surface


a = 1055'
e =2027 ~

0 20 40 60 80 100
Percent chord


1.5

1.0/ -


'5 o 4^= 055,
9-- = 517'
0 20 40 60 8
Percent chord


2.5

2.0


1.5
q/qo

P

.5

0







2.5

2.0


1.5
q/qo
1.0
Pl
.5


-P



a = 20551
9 = 5019W

20 40 60 80 100
Percent chord


Percent chord


- -- ----- --
-- --2.0







a = 055
S= ----4017
0
20 4o 60 80 100 0 20 40 60 80
percent chord Percent chord
NATIONAL ADVISORY
COMMITTEE FOR AERONAUTICS


_P2
--2t


Figure 6.- Section pressure disc; 7,' o I ns for NACA 65-110 blower blade;
stagger, 00; soliicyt, '..*; no ad.


Fig. 6


1.5
q/qo
1.0-
P1

.5


1.5

1.0i-
.5
.5









NACA ACR No. L5G18


o Convex surface
+ Concave surface


2.5

2.0


1.5

1.0
p-
P -
.5

0
0


1.5
q/qo
1.0
.5

.5


- -- ^-




a = 0055'
e = 10l '

20 40 60 80 100
Percent chord


2.5

2.0


1.5 -
q/q.
1.0


.5
1 -T55 --
= 202 --
0
0 20 40 60 80
Percent chord


..7


2.0

1.5
/qo
1.0_
P1

.5
o
0
0


1.5
q/qo
1.0
P1
.5


P2
P2t


T .




a = 55'
8 = 4039'

0 20 40 60 80 100
Percent chord


Percent chord


2.5

2.0

1.5


-p2t--- 1.o --- 2t


a = 2055, .5 a = 5055o
8 = 3036-- --- 8 = 6016'-
0
20 .0 60 80 100 0 20 40 60 80 100
Percent chord Percent chord
NATIONAL ADVISORY
COMMITTEE FOR AERONAUTICS.


Figure 7.- Section pressure distributions for NACA 65-110 blower blade;
stagger, 00; solidity, 1.00; no ad.


Fig. 7










NACA ACR No. L5G18


o Convex surface
+ Concave surface


1.5
q/q!

1.0
Pl

.5


0 20 40 60 80 100
Percent chord


Percent chord


Percent chord


1.5
q/q
1.0


NATIONAL ADVISORY
COMMITTEE FOR AERONAUTICS


T -P2t


S= 255,
e 57'

0 20 40 60 80 100
Percent chord


Percent chord


Percent chord


Figure 8.- Section pressure distributions for NACA 65-110 blower blade;
stagger, 00; solidity, 1.50; no ad.


Fig. 8


1.5
q/qo










NACA ACR No. L5G18


o Convex surface
+ Concave surface


a = 201
e = 345

20 40 60 80 100
Percent chord










,7 -- -
+ +



a = 4018'
e = 5030o

20 4o 60 80 100
Percent chord

CO


2.5

2.0 -

1.5
q/qo _-- T- @_ -
1.0 -
p1
.5

0
0 20 40 60 60 100
Percent chord


2.5

2.0

1.5 -x- -


P2 1.0- -- a
pPt PI

a = 8018'
0o 9 = 848'--

0 20 40 60 80 100
Percent chord
NATIONAL ADVISORY
MMITTEE FOR AERONAUTICS


Figure 9.- Section pressure j31 trl t t l:i.n for NACA 65-210 blower blade;
stagger, 00; s: Illti '..:.6:'0 = a 018'.


Fig. 9


2.5

2.0

1.5
q/q
1.0
P1
.5

0
0


* 2.5

2.0

1-5
q/qo
1.0
Pl
.5

0











NACA ACR No. L5G18


o Convex surface
+ Concave surface


2.5

2.0



1o
1.0
Pl


+. +






20 40 60 80 100
Percent chord


0 20 O 60 80
percent chord


0 20 40 60 80 100
Percent chord


2.5

2.0





0P1 1

5 .5
9 =859'
100 0 20 40 60 60
percent chord
NATIONAL ADVISORY
COMMITTEE FOR AERONAUTICS


Figure 10.- Section pressure distributions for NACA 65-210 blower blade;
stagger, 00; solidity, 1.00; ad = 4018'.


Fig. 10


100








NACA ACR No. L5G18 Fig. 11







o Convex surface
+ Concave surface

2.5

2.0


1.5
qA, --

P1 P2t



0
.5 ----------


0 20 40 60 80 100
Percent chord




2.5 1 I 2.5

2.0 2.0



/qo _P2 o P_
1.0_------- p 1.0_ -.p
pI t pli-
P21
.5 .5
a = 2018 o', L I -- a 6018,
O 0=361 = 8823'
0 20 40 60 80 100 0 20 40 60 80 100
Percent chord Percent chord




2.5 2.5

2.0 -- 2.0


l.C^-- 10--
1.5 i*-t -5 -
q/q P72 --- -p2-
10


a = 4018' o = l8'_ -
1 = 6039' e0 1 90431
-
0 20 40 60 80 100 0 20 40 o 80 100
Percent chord Percent chord
NATIONAL ADVISORY
COMMITTEE FOR AERONAUTICS


Figure 11.- Section pressure distributions for NACA 65-210 blower blade:
stagger, 00; solidity, 1.50; ad = 4018.









NACA ACR No. L5G18


o Convex surface
+ Concave surface


0 20 40 60 80 100
Percent chord


Percent chord


r+-+^ P2
SP2t


a = 9005
-B 10012,

0 20 40 60 80 100
Percent chord


cljl


P2
-^-----I----P^


a = 11003
= 12o04,--
0 20 40 60 80 100
Percent chord


0 20 40 60 80 10
Percent chord


10 0 20

NATIONAL ADVISORY
COMMITTEE FOR AERONAUTICS


40 60 80 100
Percent chord


Figure 12.- Section pressure distr!"i !-^n for NACA 65-410 blower blade;
stagger, 00; solldlt.., ...: d= 7005'.


Fig. 12










NACA ACR No. L5G18


o Convex surface
+ Concave surface


2.


P2
L- P2t
[-----a=^'o,-----^---

50355
0 20 40 60 80 100
Percent chord


Percent chord


a=- 6003'
-- = 8020 ---

0 20 40 60 80 100
Percent chord

C(


.5

.0


/qo I




.5 a= =0039'

0
0 20 40 60 80 100
Percent chord


1.5
9/9o
1.0
p1
.5


Percent chord


0 20 40 60 80

NATIONAL ADVISORY Percent chord
COMMITTEE FOR AERONAUTICS


100


Figure 13.- Sect Ir. ,.r :-re distributions for INAA 65-410 blower blade;
Est .g., rc': olidity, 1.00; ad = '


Fig. 13


2
P2t


P2
P2t











NACA ACR No. L5G18


o Convex surface
+ Concave surface






P2
P2t


- ^*- I +, _



-- 9 = 706 --

u 20 40 60 80 100
Ferc nt chord


o 20 40 60 0O
Pcrcc nt chord


100 0

NATIONAL ADVISORY
COMMITTEE FOR AERONAUTICS


PF:ure 1);.- Section :Ire sure l1tributions for -. 415-0 loter blade;
steager, 00; sol 1ity, 1.50; ad =


Fig. 14


Percent chord


Percent chord


100

















o Convex surface
+ Concave surface


0 20 4o 60 80 100
Percent cherd


0 20 40 60 80 100
Percent chord


Percent chord


2.5

2.0

1.5
-
--p2 1.0
t pt +- -

.5
o =120 l a = fl i
--- 3--- -e= ia
0
0 20 40 60 60 100 0 20 40 60 80 100
Percent chord NATIONAL ADVISORY Percent chord
COMMITTEE FOR AERONAUTICS

Figure 15.- Section pressure distributions for NACA 65-810 blower blade;
stagger, 00o solidity, 0.88; aa = 115P9'.


NACA ACR No. L5G18


Fig. 15


2.5

2.0

1.5
q/qo
1.0
P1
.5

0







2.5

2.0

1.5
q/q'
1.0
Pl

.5

0








Fig. 16 NACA ACR No. L5G18






o Convex surface
+ Concave surface

2.5 2.5

2.0 2.0

.5 ^ 1.5
q/.c. oP2 q/q .----"-! P2
1.0 P1.0 -- 0 P2t
P1 P1

-5 *5
-I f---- --^ P --
= 110191 I
o o
0 20 4O 60 80 100 0 20 40 60 80 100
Percent chord Percent chord




2.5 Ii ZI 42.5-

2.0 2.0

1.5 1.5
-/ -. q/qF
9/, 2 p2o 2
1. h d P2t 1.0 t 2 Pt
P1
.5 -.5
+ e 13027 18003?
0 0
0 20 40 60 80 100 0 20 40 60 80 100
Percent chord Percent chord




2.5 2.5

2.0 2.0

1.5 1.5
q/q p2 q/q P2
1.0 P2 1J0 P 2

55 .5
1i i- a = 14039
S= 15007' 9 = 18046,
o 0
0 20 40 60 80 100 0 20 40 60 80 100
Percent chord NATIONAL ADVISORY Pe cent chord
COMMITTEE FOR AERONAUTICS

Figure 16.- Sectron r*-E.,r- distributions 'or NACA 65-810 blower clsde;
stagger. ':-; :olldity, 1.00; ad = 11039'.









NACA ACR No. L5G18


o Convex surface
+ Concave surface


2.


0 20 40 60 80 100
Percent chord


2.5

2.0

1.5
/q.o P2




S= Roo-it
0 1 --,
0
0 20 40 60 80 100
Percent chord


0 20 40 60 80 100
Percent chord


0









0 20 4o 60 80 1oo

Percent chord











0o ---
Sc,0_--c^+----'^
PI ^ -J -I *-


0 20 40 60 80 100
Percent chord


--i T- ...

0
0 20 4o 60 80 100
Percent chord


NATIONAL ADVISORY
COMMITTEE FOR AERONAUTICS


Figure 17.- Section pressure distributions for 'PCA 65-310 blower blade;
stagger, 00; solidity, 1.50; ad = 13039'.


Fig. 17


'2

P2t

















P2
-2t










NACA ACR No. L5G18


o Convex surface
+ Concave surface

2.50

2.0 E


2.5

2.0

1.5
q/q0
1.0 ------
p1o 4-- -.-->


.5
a = 10008'
0 a =1630-11
0 20 40 60 80 100
Percent chord


2.5

2.0

1.5


1.0
Pl- +
.5 a 12008
8 = 18034
0
0 20 4o 60 80 100
Percent chord


0 20 40 60 80 100
Percent chord


0 20 40 60 80 100oo
Percent chord


0 20 40 60 80 100 0 20 4o 60 80
Percent chord NATIONAL ADVISORY Percent chord

COMMITTEE FOR AERONAUTICS


100


Figure 18.- Section pressure o ri-'r P. 1-nrs for "'ACA 65-(12)10 blower blade;
stagger, 00; sol!Jlitl a0..; ad = 1i00'.


Fig. 18










NACA ACR No. L5G18


o Convex surface
+ Concave surface


2.5

2.0

1.5
q9/9
1.0
P

.5

0






2.5

2.0

1.5
q/qo
1.0
P
.5

0






2.5

2.0

1.5
9/qo
1.0
P:
.5

o


P2
P2t


0 20 40 60 80 100
Percent chord


; i-





S= 10008,
S--- = 17015'

0 20 40 60 80 100
Percent chord











1~~~~~~~ e-*l1___^1
I


a = 12o008
S= 18057--

0 20 40 60 80 100
Percent chord


P2
P2t


' O 1 1 : 1 : I i
.0 -l- --


5






0
5 i18008
S=- 24040---

0 20 40 60 80 100
Percent chord


2.5

__ -2.0



21- Zt 1.0


.5
20- a5 = 2000I
= 2050 = 25054,-
0
0 20 40 60 80 100 0 20 40 60 70
Percent chord NATIONAL ADVISORY Percent chord
COMMITTEE FOR AERONAUTICS


P2
P2t


















P2
P2t


Figure 19.- Section pressure distributions for NACA 65-(12)10 blower blade;
stagger, 00; solidity, 1.00; ad = 16008'.


Fig. 19


1,
1/
1.











NACA ACR No. L5G18


o Convex surface
+ Concave surface


2.5

2.0

1.5
q/qo
1.0
Pi
.5

0


2.5

2.0


_P2
1.0to I
1.o --- .. P2t



= 18008
.5 M1 l08'
e = 29026-
0
0 20 4o 60 80 100
Percent chord


=12008'
= 2326

0 o 4o 60 80 100
Percent chord











-+- -- -



a = 1408'
9 = 25020

0 20 40 60 80 100
Percent chord


2.5

-- 2.0

-- -- p 5 p2

P2t 1.0 2
p1

= 1600 = 22008
--e=27026,--- = 33014-l
0
20 40 60 80 100 0 20 40 60 80 100
Percent chord NATIONAL ADVISORY Percent chord
COMMITTEE FONAL AERONAUTICSSORY
COIMITTEE F OI AERONAUTICS


Figure 20.- Section pressure distributions for N.:n 65-(12)10 blower blade;
stagger, 00; solidity, 1.50; ad = 18006'.


Fig. 20


2.5 .

2.0



1qo \._- P-2
1.0 t
i1
5 = 20008-
S- = 31021,
0 '
0 20 40 60 80 100
Percent chord


2.0

1.5
q/qo
1.0
P1
.5

0







2.5

2.0

1.5
q/qo
1.0
Pi
.5

0


L








NACA ACR No. L5G18


0 20 40 60 80
Percent chord


U


5

0


5

0
/5 -
5 --------


o l-4 a = 23
o i -- i-1 ---o- o- i-

0 20 40 60 80 100
Percent chord


o Convex surface
+ Concave surface
.o0

2.5

2.0


1-5
P2qc
P2t 1.0


*- *5 -27 =2

- T -0
100 0 20 40 60 80
Percent chord


P2
-P2
- 2t






100


3.0

2.5

2.0


1.5 -
-o ---- ---
oq/q
1.0




0
0 20 40 60 80 1oo
Percent chord


P2
p2t


3.0 5.0

2.5 2.5

2.0 2.0


1.5 1.5
q/qo 2 q/qo -
P2t
1.0 1.0






Percent chord NATIONAL ADVISOY percent chord
.P--





NATIONAL ADVISORY
COMMITTEE FOR AERONAUTICS


Figure 21.- Section pressure distributions for experimentally designed
blower blade NACA 64-(A)06: stagger, 00; solidity, 0.976; no
recommended design condition.


P2
P2t


















P2
P2t


Fig. 21


2.

2.

1.
q/
1.


i









Fig. 22 NACA ACR No. L5G18






o Convex surface
+ Concave surface


2.5 2.5

2.0 2.0

1.5 1.5 P2
q/qo pto q/- 2
1.0 *.t 1.0
P1 9i7Khttthtttt1
*5 -- = -190 .5 a =250
S-1054 e = 37056-
0 0
0 20 hO 60 80 100 0 20 4o 60 80 100
Percent chord Percent chord




2.5 2.5

2.0 "-- --- 2.0

1.5 1.5 P2
q/qo q/q- P2t
1.0 1.0 1


S5 a- =10 io -I =270
ST- = 5 305 3 = 9020'
0 1- I- I --- I-I -i 0
0 20 hO 60 80 100 0 20 40 60 80 100
Percent chord Percent chord




2.5 2.5

2.0 -- 2.0

1.5 P2--- 1.5 2

1.0 1.0
op po
.5 .5p^=^s= =
"=29 /
a 25 a = 29
35027' 0 6= i 016 6
0 0
0 20 40 60 0 00o 0 20 4o 60 80 100
Percent chord NATIONAL ADVISORY Percent chord
COMMITTEE FOR AERONAUTICS

Figure 22.- Section pressure -'1trl-,;tions for experimentally designed
blower blade t. 1 '4-1 ic.t; stagger, 00; solidity, 1.465;
range of ad, 210 to 530.









NACA ACR No. L5G18


Fig. 22 Cone.


o Convex surface
+ Concave surface


0 20 40 60 80 100
Percent chord


2.0 -

1-5
9/9q _
1.0

51

e =45048,
0
0 20 40 60 80 100
Percent chord


0 20 40 60 80 10(
Percent chord


P2
P2t








NATIONAL ADVISORY
COMMITTEE FOR AERONAUTICS


Figure 22.- Concluded.










Fig. 23 NACA ACR No. L5G18





o Convex surface
+ Concave surface

3.0 3.0

2.5 2.5

2.0 2.0

1.5 1.5 2
S- P2 2t
1.0 1.0
Pl Pi p __
5 .5

8o =28 4' I 07
0 o
0 20 40 60 80 100 o 20 40 60 80 100oo
Percent chord Percent chord

3.0 35.0 T 7--

2.5 2.5

2.0 '2.0

1.5 1.5 -1P2
q/q p2 q/qo 2t
1.0 t 1.0

.5 .5
a = 2o = 320
0 e= 31011' 0 =0018'
0 20 40 60 80 100 0 20 40 60 80 100
Percent chord Percent chord


3.0 3.0



2.0 2- ,.0
2.5 2.5 .... -- -'




1.5 P2 1.5 -P2t
qo q/qo -1.00
1.0 P 1.0
pi- ^r- pl

o o0L. -- o
00 20 8 Ili-= 0 4 5001 I
0 20 40 60 80 100 0 20 40 60 80 100
Percent chord NATIONAL ADVISORY Percent chord
COMMITTEE FOB AERONAUTICS


Figure 23.- Section pressure distributions for experimentally designed
blower blade NACA 64-(B)06: stagger, 00; solidity, 0.955: no
recommended design condition.









NACA ACR No. L5G18


o Convex surface
* Concave surface


-P2 1.5
__ i P2
t 1.0

L P
=200
9 = 32 5'
0 20 40 60 80 100
Percent chord


Percent chord


0


Percent chord


2.5

2.0


1.5l ---- ----- -

1.0 --

.5

e = 5O030o'
0 20 40 60 80 100
Percent chord


0 20 40 60 80
Percent chord


--24 15
- 2t q/qo
1.0 ---

51


0o = 48j18'
00 0 20 40 60 80

NATIONAL ADVISORY Percent chord
COMMITTEE FOR AERONAUTICS


Figure 24.- Section pressure 'i: tr :.. l.en for experimentally designed
blower blade Km';n,. -1i jC6; stagger, 00; solidity, 1.435;
range of ad, 2.,6 to 30o.


Fig. 24


P2
p2
P2t

















P2
P2t


SP2
P2t










Fig. 24 Cone.


NACA ACR No. L5G18


o Convex surface
+ Concave surface


.u


*.5 0t! .. -



!.0 --- 2t

-5e


P1
*5
S9 = 520'
0 20 40 60 80 100
Percent chord


.o
.5

-5













Figure 2.- Concluded.
,0 -






0 e 1 = 513'
0 20 40 60 80 1
Percent chord



Figure 2l.- Concluded.


P2t




NATIONAL ADVISORY
COMMITTEE FOR AERONAUTICS








NACA ACR No. L5G18


o Convex surface
* Concave surface


o 20 o4 60 80 100
Percent chord


0 20 40 60 80 100
Percent chord


3.0

2.5

2.0

1.5
q/qo
1.0
PI
.5


2.0


1.5
q/qo
1.0

Pl
.5


0 20 4o 6 0 8 100 0 20 40 60 80 100
Percent chord NATIONAL ADVISORY Percent chord
COMMITTEE FOR AERONAUTICS



Figure 25.- Section pressure distributions for experimentally designed
blower blade NACA 64-(C)06: stagger, 00: solidity, 0.932; no
recommended design condition.


Fig. 25







NACA ACR No. L5G18


o Convex surface
+ Concave surface
3.0 ri-


2.0


0 20 40 6o 80 100
Percent chord


0 20 40 60 80
Percent chord


0 20 40 60 80
Percent chord


2.0


100


0 20 4o 60 80
Percent chord


5.5

_--5--- .0p

I I I I i qI I I I_2.5

p2 2.0




a = 38 = 470
= 57033'- 1.0 67021'



S1 t I 1 1 o b 1 1 1 t1
0 20 40 60 80 100 0 20 40 60 80
Percent chord NATIONAL ADVISORY Percent chord
COMMITTEE FOR AERONAUTICS


100





P2t



2

-










100



--- P2t


Figure 26.- Section presaur 11 Ir i1 iia for *.r'- *.t*1 .- r.- J
blower blade N L-, stagg., i; --.i -, .
range of .4d, 1; '


Fig. 26


1.5
q/qo
1.0

.5

0




3.5

5.0

2.5

2.0

1.5
q/qo
1.0

.O
.5

0


r



<








NACA ACR No. L5G18


o Convex surface
+ Concave surface


4.0

3.5

3.0

2.5

2.0
q/q0
1.5

1.0

.5pl


0 20 40 60 80 100
Percent chord


0 20 40 60 80 100


L4..% 4IU u

3.5 3.5 ---

5.0 3- .0
-- P2t i -
2.5 -- --- Pa .5 .--.5

2.0 ---- 2.0 -- I

1.; 1-------- -- 1.5 -- -- --
q.o ,-- q/qo I -
I 0 -cO =470 1.0 a = 5555'


.5.5

0 1
0 20 40 60 80 oo00 0 20 40 60 80 100
Percent chord NATIONAL ADVISORY Percent chord
COMMITTEE FOR AERONAUTICS

Figure 27.- Section pressure distributions for exoerimentally designed
blower blade NACA 64-(D)06; stagger, 00; solidity, 1.557;
range of ad, 440 to 61c.


Fig. 27










Fig. 27 Cone.


2.5

2.0

1.5
q/qo
1.0


.5


0 20 40 60 80 100
percent chord


o Convex surface
+ Concave surface


2.0 -----
V I I f.o I A i I I I I I "



S 1.5
--- q/qo /q--
.. 1.0 ....

B = 77005' 10 a = 610
S= 790p32
------ -- .5
+-- --l I -t- -^ -

0 20 40 O o 30 100 0 20 40 60 80 100
Percent chord NATIONAL ADVISORY Percent chord
COMMITTEE FOR AERONAUTICS


Figure 27.- Concluded.


NACA ACR No. L5G18








NACA ACR No. L5G18


Fig. 28


NATIONAL ADVISORY
COMMITTEE FOR AERONAUTICS










0 8 16 2 52 40 48 56 64 12 80 88 96
Turning angle, 0 deg



Figure 28.- Theoretical pressure drop through a cascade at
00 sagger.


A-4
r


0
o
0
0
C ;



m







NACA ACR No. L5G18


4 8 /2 /6 ZO
Angle of alfacK,oc.,deg
F-qure Z9.- Angle through which the air 5 turned
in pc.Sing through a cacade. /VACA 65-series
b/ower- blade sec flons; tagger, O0soldi tfy, ."' S.
(Cross bar indicates c5st/gn po/nj solid
line indicates range of peaK-free
/' essure cristri lbutions.)


Fig. 29







NACA ACR No. L5G18


K


0
0


tI 1


















t1/

NACA b/o6er-
b lade sec hon
0 65 61Z)/
6 -o 65 6/O

65 -2/
S- /-/O


.5 65 1/0
X, V5 I 1


I -4-


i I i

SI I I


A ng/e of offacK, oc, oeg
Figure 30.- A ng/le Trough c//h/ch toe O/r / fturnec
in passing through a cascade. NACA 65- series
b/oa,/er-b/aode sec/ons; stagger, O so/td1fLy,
/oo. (Cross ebar /nd/cc7rtes es/gn "fpo/n2
so//d /,ne /ndo/cotes range ofpe/K-free
pressure d/str/but/ons.)


NATIONAL ADVISORY
COMMITTEE FO AERONAUTICS
I I I


i


i


~ ~ ~ '


i i


Fig. 30







NACA ACR No. L5G18


4 6 /Z /6 20
Angle of oaHlcx,oc, deg
Figure 3u/.- Arg/c through which /he ior /5
turned in passing through a co~cade.
NACA 65- series ., er-//ade sechtons;
aoqQ.-"-; Of .5o0idd/y, 150 (C ross bar
/na/cates c es/gn po/nt7 30o// //ne
/nd/cafes range of peaK-free
,0reSs're d/Str/blt//ons.)


Fig. 31








NACA ACR No. L5G18


_ _' _-:I ,T- i- ---I



. .. .1

.. .. ... .. _. _._._._i __
i ~~~~~- --- .1 -.. .....4 -


'~~--?--'


-~~~-- .J :


--- -eel
+--- t I t-'


-.. .- .4...
_- -- -
-4- --- -"-C--
-- ---
4 -- .-~ ---

~i + 4 t
--- c---. .









-rTr- T
S --L l -I- II-.I. I,- I-- --
, I, I ''. -

_.c--. ._ -- --1---- -, -:-- t-c

."t l I -- .. .





__I / Ii


- ---
,- +-. -- -* I













._ .... -' ,--
1.





S- NATIONAL ADVISORY ----
. -+--4 t .

1 '4CA bt'L/ves'sr-, ,



-- -- 4 .f LII.







NAT IONAL ADVISORY


Angle/ of aflcrac., deg
F/yu-e 32 Des/gn charr of eXper/me 7 ta/y
der/V/ed b/owaer-b/ade sectionJ at o0
tagqger. ('o/d /ines indicate recommenc/de
Tut ning /nq/les.)


r'-






Sif






PC
'-



(^
K>-*..-,
K:
K^
K


1"-


Fig. 32







Fig. 33 NACA ACR No. L5G18







i ---n _.T_-ur------i .-- ..- 4
S. ... t I

4- ...-- -- t -- +--

-'-T





S-- -t ---
-N -- L-- AV----OY ---
.... A -J --- --i
..... L : T- '



e .1.I n 1 --.


y. ...' "'3- i r-f ,A( 5:--.Y
: ; ..; : ; ; ; i- ;4
--.. .- ... .- -- r-- i i;ST --M


ure as qn chor/ For N ACA 65 -Iis-


y 8 ------ --- --


....... -_ ....* --- -
I- -T








4 .. .-.. ..... -=t ; ILL

I- --F----- NATIONAL ADVISORY
-C __O I4TTE FrO AEtONAUTICS -


0 O 0.4 0.6 8 .0
e gn G ff coefficin/, c
're 33.- D.tgn chorC fo NACA 65-ses
blo. 6/r-0h/Ce ucc o(- ; /5 aqql 0

























































































































r
IF

















































I





UNIVERSITY OF FLORIDA


3 1262 08106 509 5




S.1


























I



























i.




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