Reproduction Quality Notice · SUMMARY iräJk As a part of a programs o*' the IJACA directed toward...
64
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Transcript of Reproduction Quality Notice · SUMMARY iräJk As a part of a programs o*' the IJACA directed toward...
Reproduction Quality Notice
This document is part of the Air Technical Index [ATI] collection. The ATI collection is over 50 years old and was imaged from roll film. The collection has deteriorated over time and is in poor condition. DTIC has reproduced the best available copy utilizing the most current imaging technology. ATI documents that are partially legible have been included in the DTIC collection due to their historical value.
If you are dissatisfied with this document, please feel free to contact our Directorate of User Services at [703] 767-9066/9068 or DSN 427-9066/9068.
Do Not Return This Document To DTIC
3 ' "•i.e.- '. '•'.;**^W"V*>iS£Si---"V-*.." ••:'.'
Reproduced by
AIR DOCUMENTS DIVISION
• :!"iiil!l: ••^liM hW Üüili:1-:-:;!,. llÜlllÜlllllüiiii:
I
HEADQUARTERS AIR MATERIEL COMMAND
WRIGHT FIELD, DAYTON, OHIO
• •••'• -.'••**•„ - it
~*~i Twrr^r-y—. ••<••. T
5^ US GOVERNMENT
IS ABSOLVED
a FROM ANY LITIGATION WHICH MAY
ENSUE FROM THE CONTRACTORS IN-
FRINGING ON THE FOREIGN PATENT
RIGHTS WHICH MAY BE INVOLVED.
i
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UNCLASSIFIED
rcuirants! :'xP-£*?•~3-3^
Mitioi.iii i.o.
nc,Ji>4 F i*s_XA I
Uu ACR Ko. L5G1P
NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS
m Me. ^^ 1 WARTIME REPORT
ORIGINALLY ISSUED October I9U5 as
Advance Confidential Report L5018
DATA TOB DESIGN OF ENTRANCE TAKES FROM TWO-DIMENSIONAL
TESTS OF AIRFOILS IN CASCADE
B» Charles M. Ziamey and 71ola M. Lappl
Langley Memorial Aeronautical Laboratory Langley Field, Ta.
jr.- m 9 r \ FILE 00 RETURN TO
Special Drcume.i.s Bnnch - TSRWK--6 Wright Field Kelcrance Library Section
Air Documents Division-Intelligence (T--2) »Viignt ritld, üajiuu, Unto.
NACA
JUl? 11947*
WASHINGTON
NACA WARTIME REPORTS are reprints of papers originally Issued tu provide rapid distribution of advance research results to an authorised 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 not tech- nically edited. All have been reproduced without change lit order to expedite general distribution.
L - 188
I- NACA ACR Mo. L5G18
NATIONAL ADVISORY COMMITTEE FOR AEROHAUTICS
ADVANCE CONFIDENTIAL REPORT
DATA FOR DESI«' 07 SNTRATICE Vi»NE3 ^ROM TV.'O-DIMENSIOIJAL
TESTS CF AIRFOIL'S IN CASCADE
By Charles 1,1. Sina-vey and Viola I.:. LappI
. . SUMMARY
iräJk
As a part of a programs o*' the IJACA directed toward increasing the efficiency of coir.prespors end turbines, data were obtained for application tc the design of entrance vanen for arial-flow ccir.ps?easors or turbines. A series of blcvror-blad? reotlcn? with relatively high critical ."feeds have been developed for turning air efficiently f-j»om 0° to 80° starting with an a:dal direc- tion. Tests were wcüe of five FACA Co-lories blovrer blades (modified JACA 35(216)-010 airfoils) &nt of four experi-Tiantelly desVxed b3o*.ver blades in a stati'./iary cascade at lov rrach nu-nbar ?•. The turning effect4 v-eness and the pressure distributions of these blade sections at various armies of attach were evaluated over a r-'.ige of solidit'es near 1. Entrance-vane design charts nro presented that five a 'oltide section and ar.ple of 'ittRck for any desired turning" angle. The blades thus cifttlned operate v/ith peek-frro pressure distributions. -V/proxi- itate critical Mach,r".;j" pers were calculated from the pressure distributions.
I
M V i"
INTRODUCTION
Previous Investigations of airfoils in a cascade (reference 1) have attempted to ai^iulato flow conditions through a rotor or e. stator involving a pressure rise. The present Investigation has beon rade to provide Infonv-itlbn concerning the flow through entrance vanes Involving a pressure drop. A pressure rlt>e from the leftding edge to the trailing edge Is accompanied by a reduction of velocity relative tii the blades, wh"r<3P.g a pressure drop is accompanied by an incioace In v. locity relative, to the blades. The object of entrance-vane
H .W^k&'" £*?$£•• -tot:.;-' ' V«-?fci. T^-^NK.,5 ,". .-<: V^:. *• "^V.->
••?•-*VW,-* .>••»•••
COHPTBffi.'TIAL NACA ACR No. L5018
design Is to turn the Initial air through a specified angle with a minimum of losses. It seems likely that critical speeds could bo Increased and boundary-layer losses decreased by eliminating velocity peaks; tests were consequently made i'or tv«o series of blades to obtain a ran^e of turning ancle for a riven blade section while maintaining a pressure distribution without peaks. The tests were made in a two-dimensional low-speed cascade tunnel at the Langley Memorial Aeronautical Laboratory and are a part'of the NACA program to increase the efficiency of compressors and turbines. The purpose of the Investigation was to develop efficient blades operating at O-"" stagger that would turn the air through angles from 0° to 80a.
SYMBCTJS.
q
«1
V,
AV
»I
p2t
angle of attack, the anf!le between the initial air and the chord line of the blower blade
deslph angle of attack of blower blade in cascade
local dynamic pressure
dynamic pressure of initial air
dynamic pressure of air behind the blades
mean dynamic pressure \ -± — * *• " . • , ) 4 '
velocity of initial air
velocity of air behind the blades
nit an velocity of air ( 2 vector sum of Vj and Vg\
vocfcor difference -f velocities
Initial static pressur" iVl M
st&tio presiurf behind the blades, equal to atmospheric pres?ure
theoretical static pressure behind the blades
CONFIDENTIAL
fl
ITACA ACH No. L5G18 COMF1BESTIAL
ÄP
a
9
c
altl
P
M, or
*8 X
pressure drop across cascade (pj, - p., \
solidity, ratio of chord to rep
urxle thronet, which air is turned by bl&de3
chord
theoretical Ges.!f-;n lift coefficient of blade in free air
ntajErrrer, anr'e br. treen j:err.i;rdicu!!ar to cascade and entering Jiir
critical i,*.:%ch n-Mfcer, Ptroa-i "ach ru-nPer at which tbe velocity of eourd 1? reached on the Made
aiorn-aectlorjal arei 01: -;r_'.Jt!*.l t.!r ntrean
area of air ftrc-nr1 behind hi^.f.3
chord:;?, rje tH::tan':c f;'or- leari'i\r eego
vertical di.~tar.cr; fror? ch;rd
!
APPARAT""} AiiD TL^T ?"CCEDCK3
Mv3
The two-äJniensloiinl lov/-.»peon. described in rcfei'Pi.ee 1 has Leer, r variation of the staler anrüt a:;d This charge vets made pofplbio by co removable circular j-l^trp trut coul tlie prorent testa, the cwssciit: tunn fied by elirr.J r,e.tin>' til's boantii-ry-l on the v-iills;- however, well ra^a, i boundary-layer Elots vi fci's floorr-, the top fcne. bottom trader of U:e •.-•si: A vertical crors stctiou of i.he ap• matic-ally siiov.-n In fi/rure 1.
ca eb'J all-, r.st .0 ?• el 5 er v-v. 1
cade lit fc
of ructi R rot -.-•••• n r
COl'.t ch se "t le 'Je a;: .r.nr .1
rjrnel o ptrr ti.e so nt: v, :" 1 ^ ** •jrther r -. 1 ay r-'sd a ft bet d the
-ch-
it lidity. If «itb For s.adi-
"te.Ti
i;csn floors.
Two far.iliep of "clover bleäos -. &re invert.'fated. For l0'.v turnirr an^es, the *?ACA Cir-Perip«! Mower-blade sections were used, v.hereag for t-.i-rin" i'.r^lor greater than 30° a series of exiieriT^.ntally derived blov.er blades was used. The SASlk 65-sf-ries blo'/ci-blade sections O-TACA
Cu?P INITIAL
'#•
3}
COHFIDE-iriAk ITACA AOV >. LoGlG
6E(216)-010 airfoils with m thloliened trailing fif.o) eaiübsred for lift coefficients >f 0.1, 0.:-,, C-.-l, 0.7;, aiid l.i; veru tesfcrd at «liriitioT ?f ü.:"*ö, I.CO, -.r-.fl 1.50. The-;ö theoretic:! desijvi lift ?-f f f >5 enf •? an for *3ol<?t"3d profile-. In free ai;-'. TI'.c raet. obtaln'r.f the ordinatOE of bl&.3<3 nect.\or:f? IT? sf.ee b".nin thie.-rness nnC vavyin.' c&rrhtti-g \a rvficv.ro ?•. The orclin? t«s for i'5 tt.-teJ nve <'Jven .'r. taMe; T t^ V the?e blacor are rl.-o'.v.i in f'.'ivro ; with prevljua KIT:- (re^err-noe li , wap unco. The span, /.vr-v. -r.-.v, •vis because cf the slirfttlv ü.l*":''(.re-.o t\'.ri.icl selw
jf b tin: 'vi-:> In
I • c;e '-^c ti yj\"- ?'ns sections of rt. 5t".:ei» to ;pr.f7TB
2ncrested ir.=hc2
- J *-•-- j.'
! hi ot.de of five blower hl'idas v-ir> \:«f.'. till the ttr-ts.
-•'•"$£
"e.&xi line- th;,t (>-,: W;-hsr t'-r-nl;^: ü-.; H'.' with prak- free presrjre dl.'.'tri auil rn': '.»ere «^'cr^er.-talZy derived,. Cr.scado tests of flex Vole ;--li tes ;;t pjl idii-icü of tspproxl- nately 0.3 and 1.4 were or?.-; to detcrMirse iiTir-lir.c shapes. Thi;!>e v: I »ites 'xre r>,l* ert;i'. in c'r.a.t vr;til fc pres- sure di-trlb-tJ in v;Jthu:t pi-aV.-p \.ur abif.I^'jJ.. "?o:.: these tests, f-j-.ir "haper (.•".f. •.'•) verr. -«-lasted ar KüR lines for -.ilsc'os L"r< j"vtr a •ar-..-'-- ;.-f t'^n'ur* tr.;'ls fi-op; 20° to ÜC"-"'. ''.'he orcJIn.it«. r v'v t.-.*sre rr.-.tir. lints (desl.^.ated A, P., C, ••ii:c" D) f re f'if. :.» VsWf- VT. rlade sections were des'.fred • .*• •: v.>;.'.o 1. >- i "on::."« t'.J c',:nc-r"! with thn varlov.s r-fcr. Ur.es {:"j.•"'. <) . 7he tn.rlo t:Jc;<noss for tii?? ^kZ\ 64(21S)-00t." ai.-f:il ".-etior. with •* thic.'tcned trailing f dfre was ved. ihir rcotlon quf or. .IFen rntiicr than t?.e '.'AC;» SE-serl-äa blowt'i'-M'-nie rr.ctlar» Vc?.-v.re tl:e KACA ß5-seri«E a^f.tion f&vo thr-"-3 j.oir!'..r -f rev£r:>ö curvature on ths üyvei» Tvri'aoe. .jy c?;;>.:v:i..i,r- the i h*.?.••-;ie?p v»ith a "re;-, lir.e aocordirr: to t.'ic •"orvo-iti :'•••••.! ::=.;t!--iil (refererice S) , a ';"!•:' shi-rfj lr af.: IM,'.
- •'J•e; v.-'i" -V.ta1 :-'f :J ; -.irnce,
the r.ei:: lint latii'i- ty:-;,' tlif. p'ord wir riJvl'"r:c: lr4to tVie IJACA sttliCiurd -tMt'.o:;? ••:?.-;" t:'C 'is-'lc thj.rVr;^?« was-t'p^l'efi perpi-r.dlcv.lar to th" MC..-.-; 1:'I:' .it !.iit.?-j • -•!:;; ?. ?ht or'tiriütfis f-^j' the ofrlv-rl "eci i-nr., r.hinJ: '/,:re t'.?'.ec at solictit' fig of f7-r-f^.\?r3 bcly C-.05 an:: 1.10, ;.ri-; river In tabJcs vii to :;.'
It war .j.-fjarwl that the iritln.l slr-f3yj» di i-c-!: ':~n was parallel t--> t!'-i. tir.-.cl vails. The t-tal cut static pressures were nieaanred by totd-ieur. tu'orp on the florr and celling of the twn.iel and a rov; of wall static-pressure
CCrpIDS,rTIÄL
'k'/fc
NACA ACR No. L5018 COHFIDStfTI/J,
orifices located -p- chord le.ncth ahead of the blades (fig. 1) . In all best" the central blucle mar equipped with pressure-distribution orifif.ee.
The angle through rhich the sir wns turned by the blades was measured approximately r: chord ler-.~th behind the ble.des. Measurements were -ifc.c'e "Jith a cylindrical yaw tube provided v.itii v. fixed unc. Vhe tube was 4 inch la diameter vith two static-treasure orifices at an included ijj.'le of C0°. The ar:;;le of the arm with respect to the iilr, rhea both tubas read equal pressures, -»as found by callbratiir:. The "nu31" Method of taking wa.:.,uro'".ent" v:as u.-^d; Mint is, the &ra vras ad.jurted so tliot the tube-? t- v.hloh tho two oi-lficf.s were connected read th<5 sa.ro ami then the inrle at which the arm was "et v;ts fc w.C. with e'i ^rvcliriorefcT (an angle measuring device) . An average t^rian-' r>nj;le was obtained by surveying the i~cpp .•^.Jfcftnt to the central blade. The
1 o experimental accuracy of the turuin/: angles w&r i~ for
turning anr-los up oc «v-ort 50' £:id decrea.-od to ±1^ for angles fror, about CO0 to £0°. Tnose t'}sts 'ere cor.'.iueted over a runtje of Reynolds numbers frem iOf.OJü to Z:l0,000..
RESULTS i: I»T3CT.:3STON
The blade characteristics aro based on "r-fian air" conditions a« in reference 1. The r.ran velocity V0 (fiß. 5(a)) is therefore usod as a ba3li for dcterr-iinlng the ir-ean dynanic pressure- 0-5. Thr. pressure ti; str'V.utier.s for the different blower blaüus at various a.i.-leo of attt-ck for eacri solidity ürt sh-.iv.'n in figures 6 to Ü7. The quantity plotted Is the local C-jn^ritc i;rtssure q iJJvlded hy q0. The accirac; of th's.:«) resultr: wt.» impaired by the thlc!: boundary Isyer nlo.v. the vail.7 en-3 the :i' f fieulty of neasurinrr the eitranoe velocity -'.'or tht hlr-1; t«rr.Jn,3
angles. The b?.rjndary laye.r, which vas at tLv.f-s ~ Inch
thick, was due to the length of the turj:sl walls ahead
COrTTOElTIAL
f
I M V
•;'•. • ; t^.'itejLA'-'-'^!^?^V' #fov3*V;-Vi , ••.,•.. ;&?,;•?.. £».'• fct;;:-•-••"•'"*>.V / •.^Bftj'.^i'*;'v?
—.•U~—*—i~
^S®-^
1 \.
•'« .
: •.•.h:.^'-":.^ *
COWFIDSMTIAL 1IACA kC.ll No. I.&A13
f*
of the blades end the Interference of the blade attonh- jn»rtts. ITlgh cr-glüf! cf ntti^v throttle-.1 the tun-IT". : hr.nce, the velocity of *"be a.'i- i.ies.tv' jf the c .T.-O.I»:C w.f roJ'ited nc/ESlficra').L,v. S.'!'cs tV. iibnflute trr-or of prcav.iro rraanure.'S'stits it; ccni.'-tu.-it, £• c J3-.rJd:rnMs rcduot's/i In inf as-.irr d initial c<ynu:".tc ...v^PDare CL-I.'T:! f lea the error In r.tte^inlnf tJio i.-en-i i'yri'-'e rjrcr.-<n?f;. T'iO tfjEts, iW.i'Oi'rl-c, do njt- rl/r f-l-o uftuil rrti-is-'i: >:.i tit- bliüfs noe i-ratcly o!>t. t.r.r.- rr..?-'lt«i ^s-v ;;•* iisra to select pressure -ilr.tj-lbit! j.-i- «it-v.'Vt ; «s f.':.••.••• •
The t'-eoi-f tiiu3 pvt"su"e c'"li.irt- ä:i^ 1:J « carjeude of blü-des, if no Qr.zrry lories ».-.ud Inc.yrrJrtfFSlble ilow are assumed, car. be Ci.Jcv.lJ.ttd fro:r t".:o fj:Uov,'.!.-vr equation (reftrance 1) provJcci the tuj-rir.f f'.nflc is 'in,iv.'n;
41 I COT In-jrT.-rrrj-j
For'p = 0° («f. 5(b)),
*11
In flpure £8, the theoretical uresvure dj'np Ap/q-i
for varlsuo tun.In.:: üTI/TIöK l.i •;.;>v?;;.
It n*y bo nsted that In tl.f; ci t: af the CK;< derived b^orsr bludon fai- M-h 1 uru/.r " i.-j'-les (1! end L7) the th:}*setl".ul
;tr bis
Maries Of ?Uti'
pts'. ic- -pr i'ii'ü-i .-teil.;
i.ir; i f r_ l no
rrlisertally
tiie
',,i'(:s."i..i e« c/i .>se vuliic!
fl^'.irts " to 27. ".'je t:;,.- fou.id by Mciriiii'' the thiori. inlt.'ul static pres-- ;re ;
by throttling o." tlis f'.'i,y the eciiiafc! T u."' r; t-^ Pole., dlsßi'epancy in the ln;*.-f :. chaiigo In tie oilcul.-.ted r
••.O
ti:t:i «
• t-i .fin
•ur'icrf'. rls t >i very
Los of
•a*. c o vt.-i.-y lame )t.e -Jf: -)
m
HACA ACH No. LÜÜ18 COITT-IDTJirTXAL
For each blade sect!on, the rpnce of an<;le of attach that f-Rve pressure diPtri'oution?; without undesirable peaici «vas found. In the cnse of the K..CA 65-pc:ri.er blares, the anfle of attack Irhet .•rave the n:a:;ir.ium turnin/ aao:le -.»ith a flat i.rescyre distri- b'jfion ••»•es <•/••! p^tcti as the r'.e.-i^ canllti-n for a given solidity. This anfle ic. Libeled as de.-ign ringle of attack in liri^f-r. 3 tc 20. Fbr th3 experimentally deal"ri':d sect?on<5, a rsinjre of desfpr ar.i'le .if attack vvts selected froa the ätsirable nressure distributions at the hiphor solidities (fi.£:s. 22, 24, 26, and 27). These twe st-rie? of blower-bledo sections, with rela- tively hirh critic&l speed«, will efficiently turn air flowing ir. an axial direction from C° to 60°.
It fs seen fron the pressure ai lower solidities (fi^a. fcl, £3, and velocities are vory "nueh lov?(.r than velocities on the top »nrface. The are therefore nst *•eo-inrcsnded for in which i ifh exit '!--rh -lurhers are mc turning frjrles for various urrles of lu ii-ures C* to ?.^ a.-id tha turniiif nei'ded ere i'lr'dcaf.ed by cached lines range of soliclti'-? tr:?ted, ths care characteristics of the infinite soli
atr-ibutions at the 25) that the exit ehe maximum local e blade .rections s filiations in Tuntere^. The a! tue-: are shown
angle3 not roccrc- . V/ithin the ado of blades showa dity «.:(! H * 1-
The r'ata of the TAG .A. GS-ferieo blades indicate that i'-^v low c"<:;.5.! fi,n n.a?;;bers (cj , = 0.1 and O.a), the desi~n an^lo of attack depend.* l.i"ttle, if any, upon solidity f->v the T-ac^e of s.1! c"it;. covered in the present test?. For the hJrfcer-CG.Eibered -;t.'Cti;inr :e.j . - C.4, C.8, and 1.2), the an;'lc of ctt-.i:)' fir optiMuir operation ia essentially inüepor.dent ;f FoH'iity fo:1 tha raage from 0.8£ to 1.00 hut v!tb tin increase of rolidlty to 1.50 thn optimum wfatlr,; -r-rle ip increarec". Thece r-esults aro expected becunre fir lo".' camhrrs -r. inure as<j In solidity •sr^ü'-'.e-ss little ^.hir.f.s of turning M-fle ij-d, therefore, tj-.e- dirccfc'on if rean flow is sij-.nEsd ';rly slirhtly. Per hi/-h canters, an increase jf .solidity increases t".e Cuminr sv.rle t.p'jrecii'o.1;.'. This Increased turning; an~ie ch-MVij.e^ the :*!".fir flov." ii c? to e'ecrrase the anrle if sttucl; o.t' the blades rel'if.i'-n t,; the rtar. flew; thus, for the hJ^k-o«unter blE.dea. t"io arirle of attack i'sr optir/m operation muse he li.creared with an increase of rolidity.
COHPIDtniAL
• \AZ -• • ••
••"'*Ä
C0is?IDTE7TIAl KACA ACR JTo. L'-.-'lO
At the low solidity of O.es, the dnte Indicate that the change of turiiiiir arv.l.e w* th arfle ;>f at^ark is preacer for the KACA CS-C.i.)10 t j eJe thjn r'or the lawer-eauhered blaler In thl' •ides tie :'u"f;.'*! 'ar th.1 a difference Is rot. known, i-lt'i-ap-'i this h'.rh-cWoer blade irAj actually he -i.jre efficient 'it the «solidity of 0.8fl or the dlfftre-ine My be due to t..':;_:-•!••-.;.: ti.l error.
'i. ' •
i.ic',;; there.fore, the; use f.l 1!l"tif'13 RO'lld rot If: depli— : iv:.c tln.t 1" c-.Vv-'.i". d *v/
no fie for 811. ^r^l';:.) o.! tiieso bluc'es for hi.fii "'••^l. able. The anrlc-of-s.ttaoii pror.'.uro ciSoir:''v\it:;...i-;; wltho-ut ; c;v..» vf the "-", CA CÜ--210 bla^.e, however1, ovorlupr- puffirlenSly tj cover the turning ivnrla eori,oni;OiiJ..lrf; Sfi the ('es.Irr-aiv-'le-o.r- afcteck ran^a of tho i'ACA C5-VI.0 "ol:vie.
Examination if th*» ;:rc?;;v:i'< ;i* r til1. V:T lonr of the experimentally (Jes.l.'-ned "oJsöe-j if.io'.vfl that tü3 hlaäos operated thron/'h a wlf'e J-".r.£" of rui~ls of attack with pea'.c-frei; preenvre >1! rrcriWtlMrs. '"he fl.-it pistes used to derive the -itan-line n! fito? of tho.-e lOkdes. had e very mirror -v tr .U'r.." ('-'UJ/'C lecture of the sis.-irp leaalnr; eiife.
Apj;ro.xijnito critics.! i.:;.qu nu- .>er? (|
"üT?1O ;Ci) were obtained by ur<<; of the vw 7'j'uvuir;-,'rJen em; .it.'. uns (refri-enee 3). The value of 1/1^ ?or calculating the critical "•;,'. eh lurtf-r vug taker. fro*1! tie ,:-i»essuro distrlbuticns I'rr
'(j or tie Mr'i.'-t ve.ioelt-' point
In the de.-lfn r^rfe , Hnr.\* no r-, or ravine } :• lnd!oEted, tb"- vuluo :>f l/q... ».ais itJejti ö ":-;<m -a peak-freo prosavre (U^triVvtioj!. vhe vuVii^ •>.'"• ^/l-, In n,-.ch p.lire, •.•;ii,i oViOfen vr.?r. i.'.thor the "<.o'.c r&üue of the j3r-.r--ure ci^.rit'j-;! rvs or the th:ovf:t.1.r;;.a value et the t?r-i.!ll'v f.d-re ile-v.:r.:'.ln > vn ijh'ch ",'.-.• thi. Icr.-^r. Interference effects n-aJu .it I:.;],-:??Mile ';o f.Thj.i.it'? the criminal :*c.ch n.nbnr to 'he ?.*!;..( cie/'i'tr! j:' *-e-r.raey i.e. la !"i"w ^o-:>3bl'- for irolT,trd airi oil." "-.it i-r- an-.-ro.':l- n&.t*.on to fie ..-r't!. :al :-^'.,Cä no.- ;;•; ;•!.;;, 7"t ;ipp;ars' fro"l tV:e?!<: ttpn;--o>..l-;-tc ';....! orlut*.;:T..T !l*3t !hc o:'itInal I'ach nurrher t'-;i>'".'; t:. le L'.c;epfi-....r:r.t ...f t?:o .-oi:61ty. A? .nny be cxpjcted, the b^.udes wlt.i levv tuvrii.-r .'irylfe had a M.-'.her critical ^ae:. i.-jii'-ir-r tV.;-.n the bind es with high turn.l.nr uncles.
CCNi-'J
II I
%*•
"S*v#'; •
NACA ACR No. L6G1G. CO^IDEI'TIAL
APFUCATIOM OF R25W.T3 10 E'Ti'EiAiJCE-VA'JE LESION
m<--*i
The data obtained pre »resented in figures -~2 aiid 33 Jn Corn,s .Intended to -permit turblrs r.nd eorprosror desi'mers reedily to select entr'crice vaivsi (entering air assumed to be lloa\nr ar'.lally) for s specific rn.ichlno. Two distinct Jeri^.j prooeüirse are presented. T-'irst, 3n th«* el; <•• of 1 he lover ti.rü^r.c angles (<C0-) , ti-.o I'AC.'i FS-?tTier; Mrvej-Mu,^ roctlons can be recour-ended. "'he carter i:.c: ancle of attack to be ured to obi-fMn-u r-ptc'llefl \,nv^'j:.;' n-., le with a peak-free pressure dlrtributi.-'ri car. oo fouic: froti figure 2.2. IMs '.' e r- * r-j. eivirt. dv; = ;;.t c-:itr. ;n äuta for turr.inr; t-rrlea lers:: t:-.in f.iout 4°, bi-!. t-.^r-se angles can be obtained directly fror.-, the l,j„*ii?r..'' .in; Is tnei prea3ure-diatrib.itJon nhortr. ?'.v t,-v>11 cot'or of the design e.hart rcay '-e ll.'ustr'i.U-d .".a follovs: Sap,jose it is ücsireö. to turn ".ir rlov.'lr:,- !:i an axial direction 20° by uto of a i'ow of blauer with a'polldity of 1.35. Refer- ence t': fipure 33 --horra tl~.it a blower bledo eambr.red for a lift coefficient of C.JS5 indicated and thit it rhorld
i-.e1 The method bo operated nt an anrle of attack ot of deaifninf- rucü a blr.de ir riven in r^fr.rcpce ü. If some choica ' s avc'lable In thv. soliöU; t .i be used, it is possible to avoid c.;rputa.tIono ty aä.'ustln-; t?v> solidity until flfure S3 indicat'.s thft a » IT-VOT? blade of standard camber could be used.
In order to derir-n entrjirce vanes for t!?rni:\r: air through anfics greater than SC°, li'ure 7.Sä can be used. Four sntranco-vanu sections have been developed that, If
V.
used a*: 'ha appropriate solidity aiid cover the. turiilnT-fiiUile iant:e cf 3u° to
•:le oi' at>.MCIf. .-' r.r>0
lires represent re(.io;i~. in free pressure d-lsti'lb^' -nn; th, de.iired to turr. air efficiently d->tie either vi tii a essence o",;: at an c.nr/le of attrc'.-c of 22. or with ii ca-c&de of "ACA £4.-(.'')•' anple of attack of 20. ln a .VI a ?••
lb", ."olid Jcli these bj;»;-;" i-.n-.-c pea;:-
r, foi' e s.a.-,-It, if it is thvov-h ££°'f it could 'le 7i-. c !-(C)G0 '',jw.'le -(.ctlona
r-i'.fl a solicit; •JO ".:• i.iu.ri '1J ii tv
•fri,;.-it!i fit: an
Data have been obtained fro"i trsti rode on five NACA 65-series blswer-blodo nocfclor.r: and four experi- mentally derived hlower-tlado sections end are presented
CCMF1DE3T7AI.
•M.;;*
•>:* .%!'*" VS^J
10 COOTIDSNTIAL NACA ACR No. L5G18
in the form of design charts for entrance vanes for axial-flow coLipra.q&ora or t'ii-bin<5s. These design charts civ« a blade section ard anfle of atcc.ck for any desired turning an^le. The bledea thus obtained operate with peak-free presanre distributions. These two aeries oi" blower-blede sections, with roletively hlph critical spsedf, will efficiently turn air flow: in an axial dlpsn.Hn« *• «° • --" to fso lowing
Langley T-eaiorial Aeronautical laboratory National Advisory Coronittee for Aeronautics
Langley Field, Va.
REFERENCES
•;v|M
1. Kantrowits, A:"ihur, and De.uw, Pred L.: T Experimental Inveaticfitlon of Ai-'folla UACA OB, July 134S.
relirairary in Cascade.
2. Jacob?, East.nan i:., Ward, Kenneth 3., and Plnkcrton, Robert V.t The Characteristics of 73 Related Airfoil Section«' fron fasts in the Variabie-Doncity V.'lnd Tunnel. NAO«, fier>. Ko. 460, 1C33.
3, von'Ka'rmaii, Th.s Compressibility Effect* in Aerodynamics. Jour. Aers. Sei., vol. 8, no. 9, July 1941, pp. 33V-256.
CQHFIDSRTIAIi &.
it.
• '. T.'/' V
NACA ACT! Po. L5G13 CONFIDENTIAL 11
TABLE I
•üRDirATsa.KOR :;ACA 65-HO BLOWER BLADE
[Derived fror NAJA 65(216)-310 airfoil combined with y s O.OOlEx; fitabior.s and crdinates in percent of chord]
ITpper surface
1 2 \ 7 0
14 19 24 20 34 39 44, 50, 55, 60. 65. 70. 75. no. G5. 90. 95.
100
468 715 211 454
.5)48
.446
.£40
.94G
.953
.960
.937
.975
.934
.99?
.000
.007
.013
.Ol'J
.020
.021 ,020 017 013 ooa 006
.776
.924 1.177 i.figa £.379 2.920 3.369 4.0H2 4.616 5.018 5.310 5. 497 5.593 £.577 5.422 E.ue 4.SÜ7 ' 4.142 3.524 2.399 8.245 1.507 1.007
.£12
.150
Lower surface
2 5 7
10 1R
.785 1.283
516 05a E54 054 052
20.047 25.040 30.033 35.025 •'=0.016 «f>.0O3 £0.000 G4.993 59.93V 64.932 69.930 74.970 79.930 64.935 89.937 94.932 99.994
0 -.726 -.354
-1.069 -1.477 -2.063 -2.496 -2.R53 -3.410 -3.G20 -4.122 -4.338 -4.467 -4.521 -i. 4SI -4.3D8 -4.022 -3.615 -3.112 -2.552 -2.003 -1.449 -.915 -.491 -.396 -.150
L.E. radiuas 0.666
.._-. I
N/.VIOW/J, ADVISORY COMMITTEE l-'OK AERONAUTICS
C0NFIDF.TT7AL
'•>••.' ^jf-i&Qjiti
*.
i V.
'%
\
12 CONFIDENTIAL NACA ACH'No. L5G18
TABLE II
OSDINATSS pea I:ACA ee-2io BLOWER BLADE
[Ber-ived from I!ACA Cl{21G)^210 ajrl'ijl cinclnaci with y s 0.0015k; stations and oi'fiinates In pervert of cMi-d]
Upper lurfaso Lower •uufa.r.fc
0 .4-37 .6«!
3 .17t. 2 .409 4 .G96 7 .292 9 .891
14 .897 39 . 907 £4 . 3:30 fc9. 93 ft 34 951 29 9'J7 44 934 50 000 r.c Ü1.5 CO 0^7 65 0o6 70 041 75 042 CO 341 05 036 90. 036 05 017
100. 012
0 .709 .9f;v
l.!Jt,3 1.754 E.i"?r> 3.1J1 2. «26 •1.413 5.013 5. 104 5.706 0.03 2 G.lic'B C.1C4 5.973 5.6CC- 5.Ct;2 1X57 4.030
2.1743 1.924 l.ses
.670
.140
.115
L.W. radius:
1 ..5:58 a .591
.104 7 .r-Qfi
30 .100 "• R .3.03 to 092 I.E OSO ?C •)G5 V. c: 049 <*C "J." -».5 010 iJ'J 000 E Jl 905 fO. 972- a. 9Ö1 rs. 950 74. 957 "iD, J51 Ü4. 9f.:;. r:c 97a 54. 9Fi3 t-9. 9!<7
o.'sec
0 •- .609 - .f.17
-1 .03.4 -1 .202 -1 . 901 -;•'; .Z'iS _ri .592 _•/ .072 -o .4SI -.; .F.'M ^-z . 852 _•* .95<!
•r .oaa -c .924 •C .VC7
17.-3 j: Qf.0
-u 597 »;-_. cr;o
-j. Ot?l _ 5 7P - fei7"J - C2il - 1 ;9
SATTOflAL ADVISORY COMa"iTEE FOR AIiRC'lAUTlCS
COTTPIÜHTTTTAT,
., 3fci?'*S?>-JÄ?'t!:-.': •••••••': • ' *-*%&%%iZ<m% •. •••-,v-.i
f. » •-.-.:••• "••.:.-.* $k -I.--. .' J ;>-'::::" '•*• . I
> V.
V.».i$:jr,','..-:•>;' ••' .. •*.-•.-•: ,' '•. •^x^.'^i0r-^-:,^''-;si'.'--';''-
•••••5»
HACA ACR No. L5G18 CONFIDENTIAL 13
TüELE III
OHDKTATES POR ::ACA se-4io BLKVEH ELADE
[Derived frcm IIACA 35(£16)-410 v-irfMi] cor.v-U-.ci '.'.ith y = 0.0O15x; stations and OT\I juntos in percent oi chord]
l'ppai* sun'ace Lr.ver
1 2 4 7 9
14 10 21 2:) 34 2<) 44 E0 55 60 65 70 75 80 85 90 95
100
•zrrr-
.fl3
.0ÜC-
.018 ,793 .ÜE4 ,7C3
!r.?4 ,L?40 X70 ,9C£ . (j£5 !p68 , 000 ,C'fc9 CS4 ,071 ,OC2 ,C£o ,oei 070 ,0S£ ,033 o;'3
.OsJO
5: O .1 .1
?.f!4.i 1.1-7 L.O^'i t,. eG.". 0. 5Ü7 6.7«;;:, 7. C *4 7.K;:> 7. £13 7.070 6.70:?. 0.1291 t. 0.".. *.9:J4 4.238 £.434 £; .G07 3 .731
.935
. 110
L.E. racil'ln:
.f.fe.5
.f'f.7 7.. '05
!;.i-07 7.71",
10.217 16.207 iio.iee •'; 0.150 30.150 ?.j.U93 ,'c.(..-C5 45.0-3 2 CO.000 .. 4 n»: T o _• • --• 1 J.
59.9 46 G4.SÜ0 SJ.913 •.•4.91-1 7-J.319
•?.;.tis7 C9.SS7
"Ö.G66-
-.''42 -.740 -. t!99
-1. irc -1 . r £:C -l.PJM: -2.009 -£.394 -2 • o2£ .E> _ :•'/••/
-L; •ii.4. -2 '.US —i1 l
'.*1'"/ O
-*. 064 -2 ÖCZ -£ 007 -1 506 -1 106 - ijEr; - Jf-0
0;;£ HLV 379
-. I4c
_— i
1-
NATTOf.'AT. ADVISORY COnMTTTSE POn A3KÖNATJTIC3
COHPIDS-TJ-AL
M
• ••^fF*'1
1^ -MM^y^n'LJwlW'K ffij t^^J^i'Vi*!,,,^^
1 V
14 OOTTKTDEITIAL
TABLE IV
OnDÜTATES TOR NACA 65-P10 3I.OW5H BLADE
JTACA ACR No. L5G18
[Derived fr;m NACA 65(216)-010 airfoil combined with y = O.OOlfx; .Ttatlor.s aud ordneten in percent of chord]
"Jppe
0 .260 .106 .949
8.143 4.591
072 CG 9
14.589 19.629
181
7. 9.
24 29.740 34.304 39.870 44.936 50.0C0 55.058 60.107 65.143 70.164 75.171 Q0.1C2 85.137 90.104 95.065
100.048
T* purfiioe
! y
-i ... .
.913 1.130 1.510 <2.is74 i>.440 4.371
.149 0.415 ' .336 8.129 8.705 9.093 9.539 9.40'J 9.28:3 6.960 f.i.43.1 7.744 6.932 6.025
i:!935 2.810 1.312
.142
Lower rurface
0 .740
1.014 1. 551 2.857 5.409 7.9Ü8
10.431 15.411 20.371 25.319 30.260 35.196 40.130 45.06 4 50.0C0 54.942 £9.893 64.857 69.836 74.829 79.038 Ü4.863 69.896 94.935 99.CC-2
0 -. 513 -.570 -.654 -. 786 -.920 -.979
-1.013 -1.031 -1.018 -.979 -.929 -.858 -."71 -.G49 -. 456 -.190 .134 .496 • Üb 4
1.135 1.344 1.449 1.326 .916
-.142
L.E. radius; 0.?C6
IJATICNAL- ADVISORY COMMITTEE FOR AERONAUTICS
COBFIDENTIAL
• -;:v.'^ :,::>x&^j*&H&!xr;-?-y:'1W-••••• -•-.•>^.-;,••.:•:••• •:'•>%, .••.;:\, ••*•?-•> •***?••* •
'•„•••• •*':-..'-•*•>?':&n>~t •"•••*"-.,••-••'••; '•"*'.*v-'^ ' :••••%;•'•••«••• '-f\ -:.sr--- '• ' f
1 v
NACA ACS tTo. L5Ö13 CONFIDETTIAI, 15
TABLE V
0RDTNATE3 FOR KACA 65- (12) 10 BLOWER BLADE
[Derived fron TAC\ G5(21C) -(12) 10 airfoil oor.ibined with y r 0.0015x; ptatinr.s and ordirafces in percent of chord] - ...
Upper 3u;-i'&co Lower surface
X y : V
0 0 0 0 .151 .371 .£39 -.371 .274 l.«£7 1.126 -.387 .517 l.f.79 1.633 -.395
1.931 2.S&S 3.019 -.367 4.393 •1.0K5 5.601 -.243 f.. 06 3 5.170 R.13Ü -.090 9.351 6.147 10.639 .057 n.zm 7.734 IE.612 .342
19.477 M.ÖE3 SO.553 .594 24.5.23 9.216 25.477 .825 £9.Gil 10."40 30.389 1.024 34.706 11.153 35.294 1.207 ^9.304 11.479 40.196 1.373 44.904 11.£93 45.036 1.542 50.000 11.4C3 50.000 1. V48 55.087 11.139 £4.913 2.0C1 CC.161 10.574 59.839 2.273 C5.214 Ö.G01 64.736 2.559 70.215 a. bee 69.75t. 2.G04 75.226 7. SC3 74.744 2.SC2 8C.';42 l".. f 07 70.75" 2.S4 0 85.^04 f>.:.',2 G-'i. 7:iC 2.004 CO.l.s-i 3. t 35 C?.3'.S 2.3E3 or-. 090 2.J.37 94.J04 1.555 100.053 .134 99.93Ü -.134
L.2. ra.lius '! C.66C
NATIONAL ADVISORY corMi-rT-riL FOR AEROLUUTTCS
CONFIDENTIAL
}
I1
I
E:
•• »«Ill
i V
m 16 COKFITHSFTIAL JTACA AfiH No. L5018
.*% .^1
TABLE VI
BXPERIMEHTAIiY D3HTV2T HEAT T:1I?ES
fStations arc OJ •fllna.'SB lin I-eroent of fhord] ' '" 1 ' "1
X A ; 3 c ! .... i
D-
0 •
0 0
-——- —+ -
0 0 .?> .4-1 • 5t .ff ; i;. 00 .?5 .60 . as .»4 ]
l.PE £.<;« I
1.W5 1.07 i.:-o 0.75 j 2.5 2.1U £.:' 9 V!. Rf. ! fc.TZ- i 5.0 ' 3. Eh 4. se {•'•••ifl 3i.-<; 7.5 4.74 (5. 'K: 7.00 j VI. 10
10 E.fifl 7. i f; 3.3.0 i 3 4 ..;:" 35 't.OZ G.r:a 11. £1 ! 3 C. If, 20 7. 95 9.9fl l-t.::o' I 37. a 3 £rr 8. SO IO.ao 3 4.SS | 3 7.70 Z0 £. OH 31..';E It. 14 ; 3.7 • Cf=:
25 9. in 21. 05 15.00 17.0-7 40 9.Ü3 lo.iu lC-.i36 ! 1C. ti7 45 9.25 K\Oü It .riß i 1C.10 .':0 C.3o 11..*: 3.5.02 : 30.^:3 55 .9.00 3 J. tt 14.49 j 3 i. .10 eo e. oo JO. 75 3? .7U 12.03 i 05 E?.S1 J-fji': li.VÖ j 11.34 70 7.64 8.71 13 .cfi ! 3.0. ,33 75 C.70 7 .'Ü7 0.70 i S. -JO eo E.sa e.s7 u.Uü i r. . 41 S5 4.35 £.07. C.01 j 5.74 &0 ?.. 00 Z.49 4.04 ! 2.3'3 9£ 1.5<5 1.50 H.oa • 3.04
100 0 0
0 1 0
HATIG^M, ADVI^OnY OOWIT'i'SE FOR ASRCUAUTICS
-•^&^|lp
CONFIEEMTTAJ.
' i:.,"'\.-'"- i--.tiy,r.-..-. •-•»•j...' • - " . • "* ii-'V
-;. -X.- *.*•,•• '^•ü.*;*
••VI»...,
*•
'MM •<•".-•".»
HACA ACR No. L5G18 CQEFIUEFTIAL
TABLE VII
ORDITT/iTr.S 70H NTACJ. 64-(A)06 BLOSIZi KLADE
[Stctlonn and ordlnates Ir. p?i'cer:t ni' triiord]
17
T.Tpper surface ; Io*oi* Eur/'ace
X 5 j x 1 7
c C.57 0 0 .5 1.40 I.1,
-.'.:• 3 .75- 1.72 .75 -.02
List X.33 1 n:, .17 2.!} 3.65 2.£ .77 5.0 •'•;. 43 s.o X.3G
: 7.0 CG4 7.£ 2.78 10 7.97 10 Z.51 ]5 y. eo 15 4.54 20 IÜ.73 20 I . 13 25 11.4R 20 5.56 30 11.90 30 5.79 35 32.22 35 S.01 40 ?.::.37 40 C. 13 45 12.34 45 e.34 EO 12.3 7 50 K . 4'J 55 IT .22 £5 e. 56 eo 13.25 eo 6.48 es 10.47 65 C.24 70 Z. <4 70 E .34 75 8.19 75 .1.22 80 G.74 eo 4.44 C5 5.17 £5 3.53 GO 3.52 SO 1' .60 05 I.C-2 95 1.25
100 .14 IO") I
-.13 | ... ... i
L.S. I'arlius : 0.2P.0 j
ITATTOlfAL ADVISORY COUriTTlE POE ASKGWASTTCS
CCN?1"3ESTI:'J,
I *
1!
:-Äu-W^I#^-
I i V.
f 18
n
COHPIKÜTTIAI,
T^BLE VIII
NACA ACR Mo. L5G18
ORDIWiTES Ton "?ACA 6-1-
[Statiarja aud ordlr.atss
tTppsr auri'Pee f -•
(3)06 BtOPER 3LADE
in percent of chord]
lower surface
.75 l.S'5
V. 10 lfi 20 25 30 35 40 45 SO HE 60 65 70 75 30 85 90 95 100
0.7Ö 1.38
2.y7 4.42 6.66 B.29 3.58
11.53 ld.yo 3-S.ftC 11. "G 1!S IE 13 14 14.1£ 33.f:l
.1^
IP.
1 13. r:s i 10.G3
0.14 7.61 Ü.91 4. OS 2.13
.7.6
! 0 1 ° i i
.5 1 -.02
.75 i . 07 r-i .25 .35 1 i 5 1.14 1 F 0 2.06
7. 5 3.8Q 10 4.R2 15 6.1Q 20 7.13 £5 7.06 50 8.40 55 8.75 40 8.93 45 S.&8 50 9.03 55 3.71 eo 3. £9 til 7. «3 70 6.03 75 6.01 CO 5.14 *-rO 4.12 GO a.ee (jH
1.44 IOC -.19
KAOA ACS Ho. L5C18 fiOPFI DENIAL
TABL3 IX
OREIWES 70K NAG A 64-{C)06 BLOWER BLADE
Citations and ordlnates In percent of shard]
19
NATIONAL ADVISORY cocaiTTsa FOR Snng
CONPTuffifTTAL
• s«pt'J»r ^^j»^ ««<i#*
öSo^M
Lr>.'
i V.
,-Sfr
20 C0JI?TnEf!TIAL • KACA APR No. £5G18
TAK£,2 X
0RDINATE3 POK SACA 64-(D)06 BLOWER 3LADE
[Stations and ord.tMatc." In norcent of ^hoi*d]
ppar surviVcc To.vcr ?.ii>ixce
2.50 . 5.00
7.li0 10 15 £0 £5 30 35 40 45 £0 £5 eo 65 70 75 eo Co eo 95
100
X y
.nc e.oi
. 7ft
.r.o r.3b
,h0 .7E Of
9, GO
-l.CO -. V 5 - .Pi';
10. 1£.02 1 •"•. 42- 16. l.i 17.43 19.30 i-'O.cO kl.l'i ßl.ü.3 HC.9,1 £0.30 19.47 IP. 51 If. 97 It. 50 IK. 03 1K.31 10. Gl P.71 r.GG 4.51 £.21
.20
0
Si 7.
10 15 Ü0 U:!> SO 35 40 40 50 55 GO o5 70 75 80 3.:, 20 95
100
..TO
.75
.BE ,50 .00 ,£•0
i * .2:'» ! l .u: j .43 ! o 1 .50
i J .l;j 1 & .;w i .L2 i e . i.i
1 1G .18 " .44
| 13 .00 i 14 .00 1 14 .4:2
1 U . -K; ! 34 .11 i IS EV
-' 31
1 12 l1» 11. 2\> 1C.30
1 0. 11 { e. •lo ! 7. 23 ! ?• 20
4. £b r.. •io l. •31 -. 20
L.E. raüiusf 0.293
Vktlr.-tl. ADVISOivY C0V.:.;TTP3i: I-OR AUlO.-AtTICS
CONTIDSirj/i
f „ ..-.••: '-V--- -•-^•. ••••••:••• "~3iä!.."--->"""'. •.' j U*[y','!'.. -•••••'*.'••..•;•;-v;< '
21 NACA ACR No. L5G13 CONFIDENTIAL
TABLE XI
APPROXIMATE CiilTICAL MACE KtllGERS BASED ON MEAN VELOCITIES
NACA blower- blade section
65-110 65-110 65-110 65-210 65-210 65-210 65-410 65-410 65-410 65-ßlO 65-810 65-610 65-(12)10 65-(12)10 65-(12)10 6.1-(A) 06 64-(A)06 64-(B)06 64-(B)OC 64-(C)06 64-(C)06 64-{D)06
NATIONAL ADVISORY COMMITTEE FOR-AERONAUTICS
J»V CONFIDENTIAL
i
•'.'#
HACA ACR No. L5G18
•»- .-.-A
Pig. 1
&
a o 3 J
f
! \
K
^•^ ;.">-,-
,:*•> v:
•-i
23
Fif. 2 MACA ACR No. L5016
Chord
HACA 65-110
Tangant NACA 65-(12)10
NATKMUL ADVISORY ""•""H «• aiNMUTICI
Figure 2.- NACA 65-serlea blower-blade sections.
I
h r 1"
^ - » _ ' :i
"•'"'• . '^'••<,-;:"v'-.:""-?;1'V;: '« >->*' V1-! '*'IS-', :v? • '-;.±i- •' '•*;." ,'•>•'.«'..' •'• '• 'iSi-. i.'-t-iv- "
••". "i'V- :-.,,::! -V • ••{,'»?••: . - 'W ••?&•*-. A; ••••••?• -: V -,i. , 'A, *;?•• •: "••-...£•.. ' • • ' -. . •• . ' " ••;.•••'•,'"• ."'•;-".' ' •."•"• .<•' '-.'•'• ' ••' ,T\ • • ••• ..•"" I
1 \.
NACA ACH No.. L6018 *t-
n«. 3
Chord lino
hord Una
hopd lin»
hord Une
NATIONAL ADVISORY COMNTTEI m AUOUUTia
Figur« J.- Wan line« obtained from teate of flexible plataa In oaaeade.
.*'• '%•• .'***?•• ~&?''r~*:;
<• •• 'y>m^&*^-r^ry- >l'^l;.::ii^v. • •^••" • - "'if,*'. • '--.-tf-fc?. •**• " •„:..'.*"£-« nt-»'*•'":-*i »•>.** "k1»'. V -" ..wV-
•••W.
r • i
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MACA ACH Ho. L6018
•*%>
*ACA 6U-fA>06 Chord Im«
»ACA «t-fB)06 Chard Un«
JfACA flt-fOOfi Chord UQO
Chord Un« 1MGA äi-fDJOfi
C0"MITTB W AOOlMUTiCf
•7$-
, -ft-- A -.->! v%**!5"?wi58? :-^ffiv^^3Si^Ä«s^^aw^^'r4;^at** -. * - - - * S.^IäS'C'•••-•'•'•'• • • - - - •;
<:: ' • •:; ";-:v%^Ä^Äii;^'-?3> ••••: w^v»- ''•i3'^V*i/':''"Av''.^.*-,:.' > '••. .• •*•'»• ••
I NACA ACR No. L5018
ti-g. 5B. b
•vi
(a) Taetor dlagraa defining »an valoolty.
NATIONAL ADVISORV eOMMTTU m AOOMWTKS
(*) Flo» through a oaaead« of airfolli at oo stagger.
Figure 5.. Diagram of flow through a
tiiS
.1. '.. • tJr~-'^ •* •->-'-•••
^ra ;»>•„»?
»>'•.£" • -,iz*
f 1 s.
•0
•'••.»i.-./l!" -'-&
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1.» -
1.5 " ^. fr" ^ ^S ""1 •^— "v j ̂ ^i »•j,-
— ;:«?:—
oonvu Hrfaea Canaan. mrfM*
2.0
-»2t
20 ItO «0 80 100 paroant ahavd
1.5
•A, »p
.5
0
i= e- •-*' f l>
a * •"W • • 5°17'
"2t
20 M> (0 80 100
paroant ehord
2.5
2.0
1.5
1.0- n •5
!. -^
?*• 2 =J =1 ^J •= 1;
• • 2055' ... a m J° 9"
2.5
1 \
•-
-4 _- x% /
- a «
= 5°55 6° *
20 1*0 60 80 100
Faroent chord
0 20 Uo 60 60 100 poraont ehord
20 UO 60 80 100
raroont ehord
a.5 p
h -- ,, * "A, - .^ •J J2
'i 4 <' "2t
* ( a = KP'
o • 9
a oll 5'
o 2o Uo 6a 60 loo percent ohcrd
NATIONAL ADVISORY CONMTTU MI AUONMfTK»
Figur« 6.* Motion proisur« distribution« for NACA 65-llQ biowar blvdof it«U«ri 0°} solidity, O.881 no 04.
•'••'•>;'..--rv. ^.,••"<-••-'^'*;- :&"'&if;••••••. •• A ^ '->^0' ; ' :';-: *
1 V
}?-
NACA ACR No. LSG18 rig. 7
« Con« ivAM
2.5
2.0
•A, l.o
»1
sf. ~« >.
• a » 0=55' • • 1" »'
»2
"St
5 rr
1.5 r —
VS ^ ukt .5 _ a * S^i'
s • Uu59'
.»2 "2t
20 Uo- 60 80 100 Fsreint Aord
20 l»0 M SO psrewit diwA
2.5
2.0
1.0. »1
'. 'i
a = 1*55 • c >•
2.5
2.0
1.5 •A, 1.0 •' —
/
a-U0»1
e j»e 19'
1_»2 »2«
0 20 UO «0 80 100 pvreant ohort
1^0 (0 BO 100 pereant ehord
».5
2.0
1.5 •At l.o
p
.5
0
Si » r V -£:-
-i
a - 2°55' • •3° J*'| 1
2o ho so no loo paremt ohcrd
2.5
2.0
1.5 •A, 1.0.
»1
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o
i)
.-_ : = /
a = 5°55' 1 * b" lb
20 Uo 60 80 100 Perotnt chord
NATIONAL ADVISORY CONWTTU m AttWUUTKl
Figur« ?.- Section praseur« distribution« for NACA 63-110 DIOMP blad«| •taegar, 0°( «olJdlty, 1.00) no 0&,
• •' ^S^:^;f yU
•i
i •
i •i iLH-imjmn 1 'i i" ' Hill ~
*J*
i V.
"^%
2?- Fig. e
2.5
2.0
2.9
2.0
1.5
i.o. »1
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o
NACA ACR No. LSQ18
«•»
• , •=< *A? c •" != •v
* *• ^ •. 'PI1
L'
i . -o°05< i = 0 «• r
• COM«* aitrfao« + Donea« .aurfae«
2.5
20 liO 60 80 100 Peroent chord
A. i.o_
»1
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0
vc»!*-S^ifcZ" £ I --
a • 2°55'
0 20 Uo to 80 100 Parsent ehord
•"2,
2.5
2.0
q/C 1.0 »i-
.5
^^ % V .1 -' fc k ^ ,' f «•*, -P2 •' / »W
a • 0°55 - a • 3"55' 9 « a» Ob 9 • c "0 5>
20 lf.0 60 80 peroant obord
20 1*0 60 60 100 pareant chord
- ' IjS*»**'«^ •' K . "*, r
" * 'S?" 9 - 205t"
2.5
2.0
->2t
<J •* *s.
/ ' a » i°55»
6 A 6« 20 ^0 60 80 100
Ji
20 1*0 60 80 100 P«re«nt ohord NATIONAL ADVISORY
CONMTTU m WmtUTKt
?orsint chord
n^mrm I • Scat ion jn**csurs dlttrlbutlana for IUCA 65-110 blower bladot ataseer, 0°j »ollditj, I.5OJ no 04.
.'
„Vi,
3o-
NACA ACR No. L5018 Piff. 0
OOMftV* tUffM*
2.5
1.5 :E*-2 _»2 -»a.
2.J
2.0
1.5 «A, 1.0 _f
—< ^L, - * +•
/ ' a = 6°18» 1 * 7°03»
20 UO 60 BO 100 Percent ohord
0 20 UO 60 80 100 Percent chord
2.5
2.0
1.0
•5
— >- o- •*• -© «=| — — — —
t*""t ""Ilr^ t : _ __ • • 5°30i
1.5 — >- o- «• -o «5 •A, tf-,.-:il±=.
.»2 "2t
2.5
2.0
flAo 1.0.
»1 .5
/ **•
>• £
r a * B°lS< s =. OTi 8'
0 20 Uo 60 80 100 Percent chord NATIONAL ADVISOBY
CONNTTtE m MMNMUTKi
0 20 Uo 60 BO 100 Percent chord
PLzurs 9.» Metlcm nreeeur« MetMeutlone for SACA 63-210 tlawr bladtii .t.gg.r. 0°! .olHlty. 0.88| aj = fi»l8>.
I '
I ••.••. ••;^^^t-^rf& ••>•#;•'!»' <i.1 -'**• :•••••••
A&
-.*-*.;• ".•••W
• ,-H-f. .•:•••• ' fSS&etov • *
•• • >'*•• ' < ••*•.-' V*'-' * ''•' '• ;:H~;~ -.Ss^*ii^,•'•'•" ••• •• ..•• 'B'g'ii-' '••v'*^ • v' • '^•''•••v<-.!>3t .^.'"•-".'•••'TB?>:-. • •• r;%^
- • •*•;••>-:,'•• •' -*•. ••* •+j«»,t.w^'- .***£ T > V.
'. -s'"--? '•••< -. '.'*'••.
31
Flg. 10 NACA ACR No. L5018
• Qonv« •urfM* • Oono*** «ivfM«
p 3.0
«; ?
^ .• -•
J>2 *=«
a « 2°l8' • »1 ."0 U- 0 20 UO 60 80 100
farcent chord
2.»
2.0
1.0 . VI
.5
0
P" *I^^ ">i -y- -*»; 2 ^
a « 6°l8> •" • • 7°W'
0 20 Uo 60 60 100 paroent chord
2.5
2.0
1.5 •f -• -.
V £ • •J
' a •
U°l8> - 0 20 UO (0 SO 100
percent chard
<!.5
2.0
1.5 •A, 1.0 _ Pi
fc-*" - _»2
J -Vj
) 2 I
i =• 8°l8> 9 « 8°59' Ub""to
percent cfc
0 b
or 0 1
1 » NATIONAL ADVISORY
COMMITTEE FOI AUOWUITICS
Plfurt 10.- Sactlon preaaure distributions for WAfiA 65-210 tlower blid*| BttgtfiV, 0°( BOlMltj, l.OOj Od * ir0l8*.
sraseE^R^r« \, ''-'H-III*: .'S- Ci •:-SS'.:- ! • .;'
v. •%; •*•• :>!'.iv ?>•?<.- • •••«!'. '!-'' * *..-••. -- •':-.!?'%•- ... ,•*•: .::*••*;,, 'iP
-, '•'%, V - - •x."'
f NACA ACR No. L5018
^:g-!^'5C- Zrj :b »l —i 1
. _ o = 0°18> 8 * 2°jt'
»a
0 20 kO 60 80 1D0
Peroent chord
2.5
2.0
1.5 «A. r- 0r =8 -? ~^
•i
• = 1 °3 0'
»2
^- »2,
0 ?o Uo 60 BO 100 Percent chord
2.5
2.0
•A, .- e 5 »*, -»2
»1 .5
> •5; 'h
a • 1 °i»,i i = °3 9'
o zo ko 60 BO 100 Percent chord
J2-- Fig. 11
• Oonain iwfut
2-5
2.0
i.o _h
.5
0
2.5
2.0
1.5
1.0 »I
.5
s> t- -•
-, , - J s s " »; .
•^
e - )°2 3' 20 kO 60 80 100
Pergent ehord
L ^s-**-., _: -----e^K
._<£* ~. :*•-, .' l~ - - -
a • 8°l8' _
J-»2 »2.
20 l|0 «0 SO 100 Percent chord
NATIONAL ADVISORY coNwrrn FM MMMUTICS
Figure 11«- Section pressure dletrlbutlom for MAUA 65^10 bloeer blaoot otefger, 0°| »olljltj, 1.50; on = V>18'.
f
f
3^ rig. 12 NACA ACR No. L5018
•m m :-"*
2.0
1.5 «A, l.o
P
.5
^ ^ ^ £ k
V L
* i°c e> 0 20 t»0 60 60 100,
Percent chord
+ COBMTB martaa*
2.0
1.5
P2 «*•
=: v, s
x-2l z 7* ~r f
•5 1 ' f°0)< 1 • 10O12'
0 20 1+0 60 Percent
80 chord
100
2.5
2.0
1.5 «A, l»2- PI
.5
o
*" r* ^
a - «°05< e - i»C 1'
P2 >2t
0 20 bO 60 80 100 peroant sherd
g a lo lo In 100 nvoint shard
2.5
2.0
1.5 q/q< 1.0
PI
r"--T'""=; ^.-~ T ~«— - *N- 2u s k-
— s:sa'.-
2.5
2.0
1.5 «Ao i.o.
pf .5
o
t. Vr--
"-i>. _ _:_„i^_ : ^^=--Si, ^ •
2 zL ' > • 1}°0}I
! - 15° J7'
P2 if-»2,
20 to 60 do 100 Mr«.r>t ohord NOTICM. ADVISORY
COMMTTU rot dHOMUTKS
0 20 itO (0 80 100 Fsrssnt ohord
Figur« 12.. Motion prsas-ars distributions ror NACA 65^110 bloner bls4«| staegtr, 0°i iolialty, O.D8; a« • 7°0}'.
7
1 !
I » •'.••*• ••••;.. v- .y, • * . - -.. . : . •* .•>-..>--•• |
> v.
NACA ACR No. L5018
•3t
rig. is
• cone*«* Mrfa»
2.5
2.0
0 20 1(0 60 80 100 parcnnt chord
1.0. »1
.5
_J 1— -* *M
V ,> •- -V-
f •»
' • - 7°05' 1 » ("59'
20 1(0 60 So 100 percent chord
2.5
1.9 «A» 1.0.
»1
I 5005> , 6°2li
»ST- »2 \--»2t
20 UO (0 SO poroent chord
2.»
2.0
1.5
1.0. »I
•5
0
t :s:
• oopji ' 10°26
20 Uo 60 80 100 parefnt oherd
2.»
2.0
1.5 =•>
1.0 1-7.
6»03> • = 8°20'
>lSr~ rz
0 20 UO (0 BO 100 poroont chord
2.»
2.0
1.5 °A> 1.0 .
1 1 >- +~
p ^ k
/ / ... t
15
' > <• 11° a • 1 20J
„ "2
NATIONAL ABVIKMY aWMTTU m MMWWTKS
0 20 1(0 60 80 1O0 poroent ehord
Figure 13.- Section preccure dletrlbutlone for MCA 65-JllO blower bledei otageer, 0°; eolidity, 1.00; ad * 7003*.
• • * *•• STti***X L:^-- '/<••* •.•*-•" • -h*.f\i ••• •-• >•; ? ••;>'••••• 2 .. • • -• \ •^.s^4--. ^%^^i^ßQ^-%4m^e^:^,i, •¥,.• - .. ... -v.
7°*. *«v V •..• • :/-'. ;%*';
$**!*vi
•»?
• V
35^ Fig. 14 NACA ACR No. L5016
a.5
1.0
"1 .5
,
f- —
•- ^ N S ,
S
-- a = ;°03' » -a 4'
o Cecmt surfte* + Cenccv« •urf«««
_ *2
"2t
Ü0 U.o to Bo 1U0 percent chord
. x . x . x ft./' -t TXI-s V-lo p- £i *•; .'V
Pi'' - T - *1*V
. x : a
a • 5055, B » 701,1,
-pz
20 J4.O 60 60 Fercunt chord
2.»
2.0
q/q„ 1.0.
.5
a
1— — M
-•_
^ -* > '-. /
a * 9003t 1U y
-*8
20 Uo ho so 100 Pai*c*tit chorA
i&^--=S Efc^ 0». - ^iZjl. T: .5 Ii
- .: 0
7°0Ji 105«,
0 20 1*0 £0 80 100 Percent chord
1 •
-i f-1 S l/«o ',**
M ~
"1 / ^
" a = 1
' 1 1°03;
}ul V
r- P2 " B2t
NATIONAL ADVISORY COMMITTEE FOt AERONAUTICS
1 äo £0 60 100 MrtMit eliord
Figure lU.- Motion pr«raui>o ^lrtrlbutlom lor NAJA 65-410 MOM* bladvt »t»CCw, 0°| solMlty, 1.50» Od a Ö°ü3i.
7
•-•- - -••••'^•i-. •-• •*--•••$.-*:, '•'•-••^!P ."
I
NACA ACR No. L5G18
a.»
1.0. »l •5
-, ft - ~ ~ ^ >» 1 - St, LiÄi.ii '_ _ -is..
a • 8»59> > « 1SS9J _
»2
0 20 1^0 «0 BO 100
2.5
2.0
1.» "•/«, 1.0 I
• 5
_ £=___;=. _, _.-._._ "^«,.
, . -_ t, _ ^.
1 « 10°J9'
-•*.
20 1,0 «0 80 Parcant ahoFd
0 20 1(0 to 60 100
3^
Fig. IS
o eaaws nrtM«
2.»
2.0
1.5
1.0 »i
- "-,
—H
/ "~ K-*
/ • • H°5»' 1 • 17<fel'
20 40 60 BO PeMant chord
2.5
2.0
1.5 •W*0
1.0
**..,., ... - **>*.
/" ' ' L _ _ o = 16°59'
- »2
Paroent ehord 0 20 l|0 60 BO 100
NATION«. ADVISORY Paraant ohord
"«•• 15.- Matlon praaam dletrlbutluia far IUA «5-810 blonr bladai •>«•»• o»i Bolmity, o.aSi oa » 11059!. ^^'
f
M
(.•:„-.• ^ -••»,<wB&t.^^-^0M»!j*,-rft,.--r!v.-L "•* • • '1- •• •-' • • •..•,:••.•.-.• ••...•••.
•'i.*'!-
•- A , •
• ' t" '•' •:- --\-;.
*'•• ":*>-V" Vv a -Jft- + .' •• "- .' •• ••'•*
31-
>Ä^'Ä;:a
rig. 16 NACA ACR No. LS018
2.5 -
2.0 -
i/. Si- ^\ Vqo HH—\Jl—l . «. " . l'irC "^ 5S pij- -J- ° i - 6°59'
20 Uo 60 80 100
paroant sherd
- »2t
20 I4O (0 80 100 percent ohord
2.5
2.0
1.5 »Ao
1
' _-• h—.
f N
I> • 0°39'
• • 15° 27' ....
»2 •Pi«
2.5
2.0
1.5 l/lo 1.0
i PF=
p-s^ i£> »,-..
<i
" <*" ^ r
i - 13°»' a - 13°05' ~ _H
'2 '2t
0 20 UO 60 60 ICO
Percent onord
20 I4O 60 80 100
Percent ehord
2-5
2.0
C 1.5 °Ae - TJ _.- — •— -
*Ä- < s ... f •5 a • 10?J9' .
9 • 15" 07«
20 UO 60 80
Psresnt ebord
100 NATIONAL ADVISORY
2.5
2.0
-• >.. •tf\, - -- - V
1.0 _ Pi y ^ * *••
• 5 ~ • •lit» ??< 1 e 18" u*< 1 20 UO 60 00 100
Pei'oont fihord
COMMTTCI IM «IMMUTICS
Plcwe 16.- Section preeeive dletrlbutlone lor HACA 65-310 bloeer t>led«| oueeer, Cfi »oiwltj, 1.OO1 ad - 11*39'.
I
M r 1"
..*..... '.••.. -V <••• -iTi.. •":•,'. ;i;Ä •'(•>-"
I \.
•<W """• w% -^/.;,:"*'
3<K Fig. 18 HACA ACR No. 15018
• COOVM IWfMS
2.5
2.0
1.» 1/1, 1.0
1' • 5
*z i-^r 2-1 5*. L--~ - ±~
~ i "~*~* .. _± I • • 10°0B _
"" i • 16°J0'
20 ho 60 80 rapaent nhord
100
2.5
2.0
1.5 «A. 1.0
»i- .5
1* --^L,- t- - : : C- t : - JEI ,">,
i»i • • i
20 bo CO 80 100 Paroant alwrd
2.5
2.0
•A» i.o .
kTib'oSi !• - J0«151
4»2t
0 20 «.0 60 80 100
i-i
2.0 ^ 2
lA. 1.0
-»2 \ ^J, — -' r«t
) •* ' i - 16°08«
| »22°06
0 20 1*0 «0 60 Fars«nt dbevd
100
2.5
2.0
1-5 »A,
1.0 _h
a == -= •>
'S 'j
J V" ^Sl " r a • lo»08
1 • i V 10
*"»2«
J|0 60 80 faroant chord
2.5
2.0
l/%
.5
0
__ >-H
"5 > s k 1- + - —+—»
^ 1 r a • 20°0B B - ; 5° 56
!.
4*.
Paraant shard NATIONAL ADVISORY COHMTTIf FOtAOmUUTICS
20 J|0 60 80 100 rareaot aherd
Flgvra IB.- saetlon praaiura distribution« rer NaCA 65-(12)10 aleaar bladai ataajisr, 0°i aclldltj, 0.881 on * 16<o8'.
W'SSS^ZZl?^^^
•M<- • :
,•,;%<• ••$%*.•. •-. -'•-• ..fry-. •;$;:f; r*t-A ;.,.-'.'«\' >*'••:'. ^
1 v
m H*-
NACA ACR No. L5018 Fig. 19
2.5
2.0
1.5 •/«. 1.0 .
PI
<* r- n- •>
i s a — ~ - ** »
I M 10»08' 1 » nu
15
0 W l|0 io SO 100 ••leant t.hor4
aurfM* aurftM
2.0 r~
1.5 «/«.a 1.0
»1
-.„ < > 1^ s P,
- '"-Pa- .+-~ 1 —*-'•
/ •5 13 • • l6°o8'
0 1 • 23=10
0 20 1(0 60 60 100
2.5
»1
w£-I -^^r-- Z V I, s- tX". ~ - * N ..
1 - 12°08 - I . 18057,
_ »2
»2*
0 20 1)0 M 80 100
Parcant ahord
2.5
2.0
1.5 °Aa 1.0
»1
• 5
1 m > N, s \. , 1 \
— -^ 1 I a " 18°0B
• > 2lt°b0 ~ 20 ]*0 60 GO 100
raroapt chord
»2 »2, V
.' '% .**
- \- .'• *
.'"V $
'*,'.'-*' •v. ,v '" s
2.5
2.0
1.5
».0 _ 1
•5
i"":^ r ^ .^- " -' -»..• K
i » lli?08' i < ä6050
2.5
2.0
Pi •5
P2 »2t
*•
—f- •"•1 s
,' a > 2O°08 1 • 25" 5U
20 Uo 60 80 100 Tareant anord
0 20 l|0 60 70 100 NATIONAL AOVISOBY *M»anl ahord
COMMITTEE FM MMMHTKS
Pleura 19.- Saetlon nraaaura dlitrlbutlona for RACA 65-[12)10 blovar bladai •taggar, 0°| •olldltj, l.OOi ad = 16°08>.
$-
\,----y /•^••fr,\~'sr7^
iH- 1 Pig. 20 NACA AgR No. L5G18
a.5
2.0
1.5 •A, 1.0
'i •5
o
Z^I'-'-K i K- Vs- a ^_
I • 12«08' 1 . 23°2(
20 l|0 60 80 foreant abort tenant abort
«•5
2.0
!•» a/q, l.o _
»i
t£
I • 25°20
E:5E kp*
0 20 W 40 80 100 Meant abort
2.5
2.0
1.5 •A. 1.0
1" •5
1 ***-
— ^ n**l / "t r I = 20°0Ö«
• 3
:K
0 20 kO 60 80 100 fereent abort
2.5
2.0
1.5 •A, 1.0
a:"!::.:*,: F ^L —*—*- —^ \ •
,^*- "' "^ • f~
i • li°OBi 1 > 2T°Z6'
20 fco 60 80 100 tenant abort
»•5
2.0
1.5 «A. 1.0
»i .5
5 a c
a*"-- >
J "H >_ f I • 22°0B > - J 5° Ifc
""21
MATMNM. ADVnORY CONNITTIE Ml MMMWTKS
20 l|0 60 80 100 tenant abort
tlgura 20.- Oaetlcn praaaupa dlatrlbutlona ror HtCA 65-(12)10 Bloejer Blaooi atacsar, 0°| aolldlty, I.5O1 a* • 18»08'.
I V.
tfa- NACA ACR No. LS018 Flff. 21
3.«
2-5
2.0
1.0
•5
I5' • k >- ~ S 1 ^ X '•, 1
\ ""i' a »21° • • 2 9°l 92
• OCBIU lurfH« 4 Oono»« lurfaM
J.O
0 20 l|0 60 80 100 roroont ohord
9.0
2-5
2.0
1.5
1.0 »1
• 5
J.O
2.;
2.0
1.5
1.0 »I
• 5
K^ 1. r "^i.
•H
, .,-«£._
I » 2! 0 ' • • JO °M)'
"2t
20 Uo 60 do Voreont ohord
s v X
". ,
' " 1 - B 1
= 250 • 3 2" »
20 1)0 60 80 roroont ohord
2.5
2.0
1.5 Via 1.0
»r| •5
_, L
r ^l^~_^_ _ • *:
^H •
.
^ -"*~f~\ *• 1 * Jfc«l|2l
vx
0 20 to 60 Co 100 Pareont shord
3.0
2*5
2.0 "St-
*>-..-t *!*" ^
i
* *~\- 8 • jtS«
»2 »2.
20 Uo 60 00 100 roroont ohord
3.0
2.5
2.0
1.5 «A,
^» ̂ ^ p — L
^v" --
, ' __«=*'
„:fc~ ^ .. 51° ... _..
w 1 » 5S°15
NATIONAL AOVtSORY COMMITTO rot UMUUTKS
20 Uo to 80 Ptroant ohord
plffnr* fl.- Soetlon prooaur« distribution« for «xparlaantaUy dealf»ad blatnr bltdo HACA 64-(*!06; •tiffar, 0°; solidity. 0.976: no •oeapnandad daalg-n condition.
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Plfnra 2b.m soetlon prooiupo distributions Tor axporlnontally doolgnod hlooor Mod« HACA 6V(B)06| otttBgorj 0°I lollditj, l3)55j rugo of Og, 26° to 3do.
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Figur« 26.* laetlon jiraaaura dlatrlbutlona ror experimentally daalgned oloaer blarfa *ACA 6U-(C)o6| ataggor, Q°| aolldlt«. 1.LOO1 renga or 04, J28 to Ul°.
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Flfure 27.- Saetlon ppaiaiira dlatrib-it innn for erperinantHlJ; danlunad blower bio la MAC A 6tj.-(D}C,6; atajtger, 0°j «olldlty, 1.337i rang« of 04, 4I4.0 to 61*,
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Figure 33- Design chart for NACA 65-senas blower- blade sections; ölaqqer, O".
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TITLE: Data for Design of Bntrnnce Vases from Too-Dimensional Tests of Airfoils In Cascade
AUTKOafS): Zlmney, C. d.; Lappl, Viola £3. 0RI3IMATINS A6ENCY: National AuTlsory Commltteo for Aeronautics, Washington, D. C. PUBLISHED BYs (Some)
AITO-8385
cap, ACGCT KO. ACR-L5C18
can Oct '45 Unclass. U. &> tables, dlagrs, graphs
ABSTRACT:
Data obtained from tests of five HACA blooer-blade sections cod fear experimentally derived sections are procented In the form of entrance vane design charts for ajdal- flou compressors or turbines. These cbarts give blade section and angle of attach for any furnlsg angle. Blades thus obtained operate vrtth pealt-froo pressure distributions. These series of blouer-blade sections, oith relatively high critical speeds, oill efficient- ly torn olr floulrg In an axial dLrecUoa from 0° to 80°.
DISTRIBUTION; Reagent ccalos of this rennst caly from Ortgjnctlng Agency DIVISION: Pecsi' Plants, Jot and Torblne (5) SECTION: Compressors (3)
ATI SHEET NO.:R-J-3 Ail Brtr. n 0> t-ca, r-r-'llpoaco Ocpertfaont
SUBJECT HEADINGS: / Compressors - Performance (24260); Torblne bLy Aerodynamics (05302); Compressors, Axial ifAT
/
ASQ TTGCWNICÄ", 1W*\W Wrioht-Pottorcm Air rV Doyteo, OiSo
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