Bogdonoff, Seymour M

Hess, Eugene E

English

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*.“== -
e-
#Wft28 194/
NATIONAL ADVISORY COMMITTEE
FOR AERONAUTICS
TECHNICAL NOTE
No. 1271
AXIAL-FLOW FAN AND COMPRESSOR BLADE DESIGN DATA
AT 52.5° STAGGER AND FURTHER VERIFICATION
OF CASCADE DATA BY ROTOR TESTS
By Seymour M. Bogdonoff and Eugene E. Hess
Langley Memorial Aeronautical Laboratory
Langley Field, Va.
.—
Washington
April 1947 —
https://ntrs.nasa.gov/search.jsp?R=19930081874 2020-06-17T22:46:41+00:00Z
NATKNAL ADVX30RY COMMITTEE FOR AEXITAUTICS
TECHNICAL NOTE NO. 1271
—.— —
AXIAL-FLOW F.4NiUY~COMi’RESSLLNBkE DjK31C3NDATA “
AT 52.5° STMXXR MD FUR/HER VERIFICATION
~ CIJ%’JDEDATA BY ROmR TESTS
---
By Sqmm.r M. Bo@onorf E@ ~me E. Hess . _ -
SUMMARY
Previous teets of blower-blade sections have been extended.%y a
mries of tests at 5Z. !5° stagger. The results of these teEts have
been cmbined with the earlier test results umd are Tresenixd in new-””
blade design CIECL%Swhich supersede those pre-~iouslypresented. An
investigation in a tfiSt blower over a range of sta~er from 44°
to 65° has shown that ~or blades at a so13xii.tyof 1.0, the two- .
dimensional cascade data
The two-dimensional
predict the turning angle tc-within 1/2”.
3NTRODUCTICN .-‘+ .
cascade investigati.onof reference > covered
.a -
a series of tc+sts cf blower-blade sections at staggers of 45” and 60°
end solidit.iesof 1.0 and 1.5. In an attempt to increase the
accurac~ of the desi~ charts of reference 1 and to obtain a mea&&--”
ment of their ~recision, additional cascade tests were conducted
at 52.5° stagger on the NJ(JA65-410, 65-8J_o, and 65-(12)10 blower-blade
sections at solidifies of 1.0 and 1.5 and tests-were made in a test
blower to obtain performfincedata in e.qactual ro@t_t. s9~_uQ Some ___..
of the performance data obtained from these rotor tests are reported
in reference 2. Information on perfommnce of blade secticms over a
range of sta~er eagle is.presented herein and the results are ccm-
pared with predictions from stationuy-cascade ”tests.
The cascade tunnel, test hlowerj and techniques and procedures
used in this investigation were the same as those described h
references 1 and 2. Data on the rotating blades, however, will be
presented only for the pitch section (where the flow is essentially
two-dimensional end the solfdity equals 1.0). All symlmlq used are
the same as those h references 1 and 2.
I?RESENIY3TCCNOF
NACA
IWTA AND DISCUSSICXI
~tationaw two-dhm@ioual cascade.- The pressure
over tho ccmter _bladeof each of’the cascades of NACA @5-410, 65-81o,
TN No. 1271.
distributlms
and 65- (12)J.oblower bladeB at a sta~e~ of x •~” and solitities
of 1.0 and 1l5 are presented in figures 1 to 6. The design point,
tho anglo of attack at which an essentially flat pressur~ distril.wtion
was obtiined, is indicated on each figure. The results cd?the
turnjng-angle investigations of the three blades are presented in
figures 7 and 8.
Reference 1 pre~ents the follo~ simple equation for the
predictlm of turrdng angles in the range tested:
where
e turning engl.e
a angle between
aZ angle of zero
o
. ..-
entering air and chord line l
lift of isolated airfoil
k empirical constant determined fra cascade tests
The value of k for Z .5° etagger is fncluded with the previous
results cf reference 1 in the following table:
..
Stagger
(deg)
45
45
9*5
52.5
60
60
solidity k
—.
o l9O
1.00
.85
.95
975
.90
These empirical constants and the approximate zero lift angle
.-. —
(calculatedas in reference 1) can be used to predfct turning angles
in the range of’ the investigation to within approximately 1°,
,
.l
.
#
3
The results of the rotor ~sts, presented in the section
entitled ‘lTest-’bJ.ower results, seemeil to show that the original
data obtained for the W.M 65-(12)10 %lower blade at a stagger
of 600 and a solidity of 1.0 were not valid. A retest of this
blade showed an increase in turning angle of appro.xinately 2° and.
these data are presented. Ln figure 9 with the remits for the other
blade sections frm reference 1. The pressure distributions over
the center blade of the cascade of S?ACA65-(w)1o sections are
presented in figure 10.
The very high loadtngs of the NACA 65- (1’2)10 blade (tie
highest of any tested h cascade) appear to present a Mmit beyond
which the cascade-tunnel data are questionable. Very slight changes
in tunnel adjustment may stall the tunnel walls, which seriously
chan~es the blade performance. For this reascm, the data for the
I?ACA65-(18)10 blade at this condithn (60° stagger and sokhii@
of 1.0) have been eliminated and figure 9 now supersedes figure 7
of reference 1.
Curves from reference 1 which are of interest in compressor
design are repeated h figures 11 to 13 with the ~E!.5°stagger
condition included. @igures lA(a) and n(b) present the new blade
design charts which include the tata of reference 1. These charts
mrpersede figures 41(a) end 41(3) of reference 1 and with tie new
end co~ected data @ve more precise blade desi~ 3nfformatlon, If
the design turning angle and entrance conditions ar9 known, the
blade camber and angle of attack can be found frcm these charts.
A horizontal line may be drawn from the value of turning angle
desired on the angle scale to intersect tie turning-angle curves.
A horizontal interpolation for sta~er may be r@adealong this ltie
and frcm this potnt a vertical line may be dram. The intersection
of this line with the horizontal scale gives the design camber of
the blades, and the intersection with the angle-of-attack curves,
with a vertfcal interpolation for stag&er, gives the angle of
attack read on the angle scale l The procedure may he reversed to
o%tain the desi~ turning engle ti camber and design angle of attack
are known. Ih order to obtain desi~ data at eokhlities other
than l.0 =a 1.5, the yrqedure is carried out at solidifies
of 1 lO and 1.5 and the final result obtatned by titerpolatim.
Test-blower results.- The results of tests of fcm sets of
blades in a single-stage test blower are presentd in reference 2.
One of the blades tested had an NACA 65-no blower-11.adesecticm
and a second blade had an NACA 65- (11)10 secticm at their respective
pitch secttons. (Blades desi~ted as 5 =0.4 ana 5 =0.6 in
reference 2.)
4D1 additicm to
teeted at two othor
point~ at different
NACil?JtNO l ~~
the previous tests, the 8 = O.6 ‘t&ade~
angle settin~s which efJ?ectivelygam design
s@Cgem3. The results ot lm.rnin~an~e plotted
a~ainst ~taggerj at .2Uinci~e~mt~ in angle of atti”ck,ere premnted
in fiQ~7res15 and 16, The test-points are in very Good agreement
with the solid lines yredict@ from cascado tests. The deviatiun
from predicted values is less -than1/’2°.fol’most cases and show’s
the accuracy of the cascade results tram staggers of 44° to @o.
I?or casee Ln which the axial velocity changes through the hlado,
h reference 1 a moiiifie?.vectmr dia@am based on the averago axial
velocity was used for the bladG desi~. ‘J%stsof two blades which
ware designed for Jufltsuch conditions were made ~m the Langley
propeller research tunnel. l?hqs~%Hts show that for changes in
axial velocity of the ma~itude studied (30 pert ent of the en tranoe
velocity), the cascade data coul.ibe apylied
C’7?C!LUTINGRFMAl?~KS
with good accuracy.
have lean exten&d by a
series of tests at 72.5° staggwrl The results ezzesummarized in new
blade design charts which supersede those of NACA ACR NOs L5F07al
Cross plots of data obtained frcxaa test blomxc show thatj over
range of stagger from 44° to 65°, turning angles predicted from
cascade tests are within 1/2° of those obtatied frm tests with a
rotating setuy.
a
Langley Memorial Aeronautical La%oratury
National Advisory Ch.mnitteefor Aeronautics
ixn@ay Field, Ta., 14ay29, 1946
mfj’iTFwNcEs
1s Bo~dcmoff, Seymour M., end %gdonoff, Harriet E.: Illad-o Desi@ Da+=
for Ax5.al-FlowFsns md Compressors. NACA ACR No. LZ07a, 1945.
2. Bo@onof f, Seynour M., and Hmrig, L t Joseph: Performance of
Axial’.Flow ‘l?m ard Compressor Blades Designed for Hi@ Loadi~s.
mm m I’iol 1201, 1947.
NACA TN No. 1271 “
1.6 -
.4 -
b = 2’3
0 @ 3.90
0 20 40’60 80 100
Percentchord
2.4
2.0
1.6
1.2
d%
.8
.4
0
l
l
1.6
1*2
d%
.9
ll+
o
l
o 20 l@ 60 80 ma
Percent ohord
?
a = 8°
e = 8.5° L
o 20 40 60 80 100
Percent chord
2.4
2.0
1.6
1.2
dqo
.8
.4
c1
Fig. 1
0 20 40 60 &I 100
Percent chord
o Convex surface
q Concave surface
o 20, 40 60 80 100
Percent chord
NATIONAi ADVISORY
COMMlllES F~AERDNAWKS
Figure l.- SectIon prassure dietrlbutions. Cascade
of NAOA 65-410 blower-blade sections; p = 52.5°;
o-=1.0;aa=7.5°.
l
Fig. 2
1.6
1.2
.
.8
d~o
.4
0
e = 3950
0 20 40 60 80 100
Peraent ohord
1*6
1.2
.8
.4
d%
o
0 20 @ 60 80 100
Peroent ohorcl
2.0
1.6
1.2
d%y
.8
94
0
= 80
;= 9.50
0 20 40 60 80 100
Peroent ohord
2.4
2.0
106
d~o
1.2
.8
.4
0
NACA TN NO. 1271
T
a-= 110
6 = 12clo
o 20 40 60 80 100
Peroent ohord
o Convex eurfacie
D Conoave surface
2.4
2.0
1.6
1l2
d%
,8
.4
0
a = 140
e = 14.8°
0 20 40 60 80 100
Percent chord
NATIONAL ADVISORY
COMMITTEEFDRAEWEAUTICS
Figure 2.- Seotlon preeaure dlatributlona. Oaacade
of NACA 65-41oblgwer-blade aectiona; 13= 52.50;
o-= 1.5: a~ = 7.1 .
a
.
i
. . ~ . –—-
NACA TN No. 1271 . .
. .
Fig. 3
.
.
2.0
1.6
1.2
dqo
.8
.4
0
1.6
1.2
q/qo
.8
.4
0
1.6
1.2
dlo
.8
.4
0
0 20 40 60 80 100
Percent chord
o 20 40 60 80 100
Percent ohord .
0 204060& 100
Percent chord
2.1+
2.0
1.6
1.2
d%
.8
.4
0
2.4
2.0
1.6
1.2
d~o
.8
.4
0
ii 20 40 60 80 ma
Pement ohord
o Convex aurfaae
~ Conaave surface
\
(
= 16°
L 17.40
0 20 40 60 80 100
Percent chord
NATIONAL AOVISORY
COM)W’KEFMAIRON UTICS
Figure 3.- Seotlon ~resaure dlntributlona. Cascade
of NAOA 65-810blo~er-blade sectlcms; 13= 9.50;
C= 1.0;ad = 11.5.
Fig. 4 NACA TN No. 1271
2.0
106
1.2
dqo
l8
.4
0
2.0
1.6
102
d%
.8
4+
o
2.0
1.6
1.2
4%
.8
.4
0
0 20 40 60 80 100
Rmoent ahord
.-
0 20 40 bo 80 100
Percent ohord
r
a = 120
‘a= 16.3°@
o 20 Lo 60 80 100
Percent chord
2.4
2.0
1.6
q/q.
1.2
.8
.4
0
o 20 40 60 80 100
Peroent ohord
0 Convex surface
B Concave surfaoe
~2.4
1.6
dqo 1
1.2
.8
.4, {
= 18°
0 := 21.10
0 20 40 6tI 80 100
percent chord
NATIONM ADVISORY
COWIITTEE FUAERONAUltCS
.
Figure 4.- Seotlon preesure diatrlbutims. Oaaoade
of NAOA 65-810bl ger-blade aectlona; P = s2.sO;
o-= 81.5; ad = 11. .
,
.
NACA TN No. 1271
>
Fig. 5
2.4
2.0
1.6
1.2
d%
.8
.4
0
2*O
1.6
1.2
d%
.8
94
0
2*O
1.6
1*2
d~o
. .8
l4
o
r ~ h. L
i>— —
a = 8.75°
e = 15.70
0 20 40 60 80 100
Peroent chorfl
a = 120 ‘
e = 18.7°
0 20 40 60 80 100
Percent ohord
I I a = pjoe = 21.20 1“
o 20 40 60 & 100
Peroent chord
2lk
2.0
1.6
1.2
d%
.8
I.$.
0
2.4
2.0
1.6
1.2
d%
.8
l4
o
)
1
a = 18°
0 = 23.9°
0 20 4.0 60 80 100
Percent chord
a Convex surfaae
D Conaave surface
o 20 40 60 80 100
Percent chord
NATIONAL ADVISORY
COMUITTSS FORAEROIAAUTICS
Figure 5.-Seotlon preeeure diatrlbutlone. Caaoade
of NAOA 65-(u)1oblower-blade eeotione; p = 52.5°;
o-=1.o$ad= 15.00.
Fig. 6 NACA TN No. 1271
2.8
2el&
2.0
1.6
1.2
~%
.8
l4
o
2.0
1.6
1.2
‘l/Q.
.8
94
0
2.0
1.6
1.2
dq.
.8
.4
0
b
a=go
e =-17.20
0 20 40 60 80 100
Percent chord
2.4
2.0
1.6
dqo
1.2
.8
.4
0
= 180
L 24*5”
o 20 40 60 80 100
Pi3raentchord
o Convex surface
B Conaave eurface
= 120
:= 19.80
2.8
0 20 40 60 80 MO
Percent chord
2.0
1i6
dlo
1.2
L
Y~J l4
o e = 26.40
1 = 150 1 0 20 40 60 80 100 .:= 21.8° Percent chord
o 20 40 60 80 100 NATIONAL ADVISORY
Percent chord COMMITTEEF~ AERONAUTICS
Figure 6 - Seo ion reemme distributions. Oaeoa$e of
NACA 85-(I251O b!ower-blade eections; p = 52.5 ;
S= 1.5;ad = 160.
.
,
—
. ,
NACA TN No. 1271 Fig. 7
.
NACA blower-blade section
NATiONAL ADVISORY
COMMITTEE FOR AERONAUTICS
o k 8 12 16 20 24
Angle of attack, a , deg
Figure ?.- Turning-angle
m= 1.0. (Short line
characteri~tlca. p = 52.50;
across curve i.s deal~ point.)
Fig. 8 NACA TN No. 1271
28
24
20
16
4
0
t t I
l?AOAblower-blade section
NATIONAL ADVISORY
COMMITTEE FORAERONAUTICS
.
a
.
.
0 k 8 12 16 20 24
Angle of attack, a , deg .
Figure 8.- Turning-an le characteristics. p = 52.50;
6=
~~5. (Short l~e across curves is design point.)
,
TN No. 1271 Fig. 9
s
NACA blower-blade section
I I
65-(u)1o
/
/
65-810
NATIONAL ADVISORY
COMMITTEE FOR AERONAUTICS
.
-4 0 4 8 12 16 20
Angle of attack, a, deg
Figure 9.- !l?urnin
7
-angle characteristics, ticludin retest
of NACA 6s-(1.2 10 section. p = 600; m = 1.0. 7Short
line across curve is design point.) -- -.
20
16
u
8
4
0
20
16
K!
d%)
8
4
0
o 20 40 60 80 100
Feroent ohord
o 20 40 60 80 100
Peroent chord
Convex surfaoe NATIONAL ADVISWY
Concave mrface CO!O1l’lmm AcRlmAmcs
o
El
,.
FiRure 10.- Section pressure dietribut ion. Retest of
‘casoade of NAOA 65-(12)1o blower-blade sections.
p = 600; tr = 1.0; ad = 4.1°.
—
.
. .
NACA TN No. 1271 Fig. 11
?
*
1.4
1.2
1.0
.8
.6
l4
.2
0
~ = 600
/
/ ~
{
NATIONAL ADVISORY
COMMITTEE FM AERONAUTICS-
.-
0 10 20 30 40
Turning angle, 0, deg
Figure 11.- Variation of theoretical Ap/qo with turning angle for
three stagger angles.
NACA TN No. 1271
.
/
(d:g)
60—
52.5
’45 0 /
0 /
0 /
/
–60,--”’
/ /’; >’”~””/
‘ 52.>0 ,H
/
‘<50’
~- - ...,.— —
.! —-. —.. .+-”“----”---
o-
— 1*O
— — 1.5
NATiONAE. ADVISORY
COMMITTEE FM AERONAUTICS
0 4 8 12 16 20 24 28 32
—
Turnln& angle, 0 , deg
Figure 12.- Variation of theoretical llft ooeffloient””ofblade
in casoaclewith turning angle for varloua caecade oonfigurationa.
.
.
NACA TN No. 1271 Fig. 13
1.2
0
0-
0
1.0
EJ
m
2 .2
0
O*
o
/ / ‘
,/ /
/ ‘/ y
A
(d!g) “A
A f ~ 45/ g g.5
< I I
o .4 .8 1.2 1.6
!Jheoretioaldesign oz @ isolatedtifoll
(a) 201idlty = 1.0.
o .4 .8 1.2 1.6
meorettialdeal- Ot of isolated afifo~l NATIONAL ADVISORY
(b) 2olldity = 1.5. cmJUllEsFORAmWNmce
FigJJ2e 13.- Cmparlsonof UZO of bl~e ~ cas~~c at des~
conditions with theoretloti design OZ of 1801ated airfoil.
32
28
24
20
+’16
.
:
filz
E
0
,
L=l’1
,
t
{ ,/ w
/“ “< .-a
/ //
, , //
/
— TnmJ.ng 0n@4a
of attmk
I
1 1 1 1 1
04
o .2 .4 .6 .8 1.0 12 1.11 1.6 1.8 2.0
bs~ edmr (thmmtled q of Imlmtad nirfoil)
(d 201iditw Or Lo.
. .
l , “ .
32
28
24
20
8
4
n
I
I
(d:g) /
/
‘“45 k’
/
/
/
/
/
/ “
/
/
/
0
,5> N “’
/ 7
“5g.5 , @/ ,
/ ‘/
0 5 / ‘/
mrningangles
An& of attaok
,
/
/
NATIONAI. ADVISORY
Cu#mTEE m AfRmuwS
o .2 .4 .6 .8 1.0 1.2 1.4 1.6 1.8
2.0
Daalgn oambor(thooretioalal of isolateddrfoil)
(b)SolidityOf 1.5.
Figurel)+.- Conoltied.
z
o.
I
I
I
I
.
Fig. 15 NACA TN No. 1271
CD”
20
16
E
8
4
0
d
I 1 I I I
a
I I I I
0 2
— Predicted from cascade teats
0 Experimental pOiIlt Sj
abt3i~ stagger, 50.2°
I I I I I 1 I I I
44 48 52 56 60
Stagger angle, (3, deg
Figure 15,- Variation of turning angle w~th stagger
predicted from cascade tests and canDarison with
~alues obtained G
blower blades; C=
.
a teat blower. tiCA 65_7~o
1.0. NATIONAL ADVISORY
,
.
1
COMMITTEEFORAEIWAUTICS
i
.
B ,
NACA TN No. 1271
{’
24
20
8
4
0
44
Fig. 16
I I I I I I I I i I I I
u
.6
.“ M o
4.
q @
—Predicted from cascade tests
Experimental points
0 Pitch-section design stagger,
29
g6 0
Pitch-seotim design stagger,
. z Pitch-section design stagger, 650
,
NATIONAL ADVISORY
CWMITTEEF ORAERONAUTICS
I I I I . 1 I I I 1 1 I I
. . .-
52 56 60 64 M
Stagger angle, 13,deg
Figure 16i- Variation of turning angle with stagger predioted
from cascade tests and comparison with values obtained in
a test blower. NACA 65-(11)10 blower blades, 6= 1.0.
,,


Axial-flow fan and compressor blade design data on 52.5 degrees stagger and further verification of cascade data by rotor tests

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