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NATIONAL ADVISORY COMMITTEE
FOR AERONAUTICS
TECHNICALNOTE
No. 17”78
DIRECT -READ~G DESIGN CHARTS FOR 24S-T AL~-ALLOY
FLAT COMPRESSION PAN?KL5 HAVING LONGITUDINAL
FORMED Z-SECTION STIFFENERS
By Norris F. Dow and Albert S. Keevil,
Lahgley Aeronautical LaboratoryLangley Field, Va.
Washington
J~UUY 1949 ,1~ n,-yr ~ ~‘-’’,&.L1., .
-,
Jr.
I
1II
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— ——.. —.-. . ... .. —--—< . . ... J..—.——.—-..-.-,-... ,--.,..........._.,----....—-—.—,-+-.. ..- ., .“ .-
N.ATmwL Am5QRY cQMMm’mE
DIKWCWEDIHG
TECH LIBRARY KAFB, NM
InllllulllliluullllFm AERONAUTICS 011b5t102
TECHNICALI’?cYrFlNo● 1~8.
DIWGNCHER133FCIR24EW~
FIAT COMERE3SION PAl?ELSHAVING LONGITUDINAL
IKmmD”!GsmTIOIvSTm?Emm
By Ibr.risF. Dow end Albert S. Keevil, Jr.
Direo%eading desi~ charts ere preqrb+ for 24S4! alumin~oyflat cmpremion panda hamlng lungitu&&d. f-a Zk3ectiq stiffmers.These charts make possible the direct .detemdnaticm of the stress andall the panel proporticms required to carry a given intensity of loadingwith a given skh thickness and effective length of penel.
Design charts fm
Y
compression penels have been presented inseveral Ufferent forms. See references 1 and 2.) In reference 3, aform was developed which permitted the direct selecticm of proportimsfor @van values of the principal desi~ cmMtims - intensity ofloading, skin thickness, and effective langth of panel. This form alsomade ~ossible the ready determination of the proportims having minimumwei@t to meet these conditions. The charts presented in reference 3covered ~ aluidmmAU oy flat compressim pemels ha- longitudinalstraight-webY+ectian stiffeners. Sjml 1ar charts for 24434 al~alloy panels with exlxuded, strai*t+ueb Y-secticm stiffeners mepresented tn reference k, and dfrect+e- desfg.Icharts for @iHCalumbuwdloy penels with formed %secticm stiffeners are presantedhereti.
EmQ301s
The spibols used for the panel Mmexu3ionE are given h figure 1.Ih addition, the following s@bols are used:
c coefficient of end fixity as used in Euler column fcmmla
“d rivet diem.eter,inches
L length ‘ofpanel, inches
------- -—.——. . —— —-— .. . ... . . ....— .._n —__ ,_ ..___—__ .--— — ....._.__. .
2
P rivet pitch, inches
Pi compressive load per
z cross+3ecticmal exea
NACA TN NO. 1778●
+.
inch of psnel width, kips per inch
Ier inch of panel width, expressed as anegyivalent or aveq thiclmess, tithes
P radius of gyration, inches
Zf average stress at failiug load, ksi
‘cr stress for local buckling of sheet, ksi
=Cy compressive meld stress, ksi
DIWWH3MDING lXH!XN CHARTS
Direct+reacMng design charts for 2@ alumin~oy flat compressionpanels with longitudinal formed Z-section stiffeners hamlng the propertiesand proportims given in tables 1 to 5 ere presented b two forms infigures 2 to 9. Ih the first form (figs. 2 to 5), the design ccmditionsof intensity of 10*, effective length of panel, and skin thickness
21qxe ticorporated in the cmlilnate P1/tS and.the abscissa —. This
L/fi
form, hawing the design conditions hmrporated in the orMnate andabscissa, is the more useful for most desigu prposes because the curvesare more widely spaced and interpolatim is more straightfoqyard. Znthe second (alternate)form (figs. 6 to 9), the average stress atfailure + is plotted agdmt Pi/ts as was dme in the E3umMry plots
“ofreference 5. This alternate form, having the stress – au inversemeamre of wei~t for a given load - as ordinate, is the more usefulfor making generalizations * cm-prisms of structural efficiencybecause it shows how nearly the stress actually carried a~oaches theupper limit comespmding to the stress that would he achieved by a pureshell construction if a pure shell could terry the load without failure.
PiThis upper Mmit of stress is represmted by the lines for ~f=—
-tS(~~te stiffener spacing) in fi~es 6 to 9.
Values of the ratios of stiffener thiclmess to sldn thiclmess tW/tS,
spacing of rivet lties to skin thiclmess S/tS (because there is onerivet line associated with each Z-section, the stiffener spacing bs is
equal to S, the spadng of rivet lines), and hei&t of stiffener tostiffener thiclmess H/tw, which will Satisfy me desi~ c~lti~s, ~,be found directly_Qmm these charts, and the correspmding secticmproperties Ws> ms~ * p/ts may be found fram tables 2 to 5. ~
— .-———-. ——~= ...z ~,- . ..... . ..,,.,-
.
NACA TN NO. 1778 3.
\
the first form of design chart (figs. 2 to 5) dashed lines are used toindicate values of average stress at failure tif;whereas, on the alternate
form of design chart (figs. 6 to 9) dashed lines are used to indicatePf
values of —. b both forms the value of Gf corresponding to theL/fi
point at which each curve is cut by a short heavy line is the value ofthe stress for local bucliling acr for the proportions ~epresented by the
For example,H
curves.sthemalueof ucr for —.21 and —.35in
(
tw tsfigure 2 is approximately,29 ksi. Only a short panel of these proportim
)
‘i ~ 0.27. ~would buckle before failme — one having a value of —L/fi
the value of ucr is so low that the short heavy ltie would fall outside
the boundaries of the chart, a mmerica2 value of Ucr is given snd is
associated with the proper proportions by a leader to the curve. The panelproporticms which have mintmm weiQht are indicated on both forms ofthese chsrts by the use of colors as follows:
(1) E the proportions correspond to a blue regim, they are theproportims which give the lightest possible 24S4? Z-stiffened panelwhich will meet the deei~ conditions
(2) IX the proportim correspond to a red region, they are thelightest possible at the ratio of stiffener thickness to skin thiclmessgiven by that particular chart, but sane other thiclmess ratio wouldgive a lighter design
(3) If the propotiims correspond to a white regim,meet the design conditions, but they ere not the lightestmeet the conditims
the proportimswhich will
Because tn many cases the proportions may be varied somewhat fromthose indicated by the red and blue regions with little change in themll.ueof the stress that can be carried, too mzch @ortance should notbe attached to the exact proportions indicated by the colors to haveminimum weight. lh any particular case for Wch a deviation from theminimm=weight proportions is made, however, caution dictates that theweight penalty associated with this deviatim be determined.
The direc&reading design chax%s premmted herein were developed inthe manner described in reference.3 from the test data and resultingcurves given in reference 2.
..—+. . . .. .._ _____ ..--. —.. ... .. .P . . . . . --.-——
.— .-e -~. . . . . . . . . . . . . . -—— -
.,.-
4
USE CM’TEE DIRWT+WDING
NACA TN NO. 1778
Dl!SIGNCEKRTS
The manner of using the direct-reading design charts deyends insome measure on the desired degree of precision of interpolation emongthe curves. For many proposes, i.nterpolatim by inspecticm is of adeqpateaccuracY, ad the use of We C~S re@es @ tie c~c**i~ of the
Pivalues of the desi~ parameters Pi/ts and — to permit the desired
I@proportions to “beread directly from the curves. The proportions formnmm weight, moreover, may %e f- tiect~ = fiose co~emmto the blue regim on the curves.
madeE more accurate interpolation is desired, a plot can readily beof H/~, ~f~ * ucr ~ W*s at tie @~~ =J-Ues of Pi/*s
‘i-_ and the proportims can %e picked frcm it. (This plot is “L/ )JC
similsr to that which results fmm the use of the ~eight designprocedure with the prewlmusly available design charts as illustrated inreference 2.) On a plot of this typO, the proportions for mtntmumweight correspond to those associated with the higheti value of Zf.
As a check on the accuracy c& interpolation, the cross-sectiaualarea per ~_h of width of the design msy be determined frm thevalues of t/tS given in tables 2 to 5 end the value of the intensity
of loading Pi that can be carried on this cross-sectional area per imch
at the value of af given by the charts may then be compared with’the
design value of Pi. .
k order to Wustrate the use of the direct reaMng design chartsend the simplicity of the computatims associated with thin, a panelwill be designed for minimum weight to meet the same principal designc@tions used to illustrate the desig procedties in reference 2,namely:
(1)
(2)
(3)
=tmi@ of 10* pi = 3.0 BPS per “inch
m ~C-SS t~ = O.@ inch
E?fective length L/fi = 20 fiches
. ..————.—— --- ..——— —---- —--..—.——– —-————, --- - ---r——.,.. . . . .. . .,. ,----
NACA TN X6. 1778 5
‘iFirst the values of Pi/tS end — are calculated
L/fi “
pi 3.0.=—ts 0.064
= 46.9 ksi
= 0.15ksi
Then a trial value of ~/tS is aSSUIned
)will be used . Ih the chert for this value of/
corresponding
lineat ~=%
( %for the example — = O.~ta
to the designPf
+alues of- P~/tS aUd. — lie on the redL/&/. \
26 ~ :=25). Accordhgly, the value of H/~ far
minimumweight for
by a red lhe, not
give less weight.
-%— = 0.79 is 26, and because thets
a blue line, some value of ~/tS
~ection of tie charts for other
value is estaliMshed
other than 0.79 will
va,l.~eeof ~r/tS
reveals that at the given design values
region lies betwe~ — . 26 and — .: ;
By interpolatim, the panel ~oportims
Hare found to be
()
%— z 28.5~% 29”5 ~
31. on the chart for ~ = 0.63.
corresponding to tMs blue region
and for these proportions ‘q x 30.5 ksi’ and am x 30.5 ksi, which me
the valuescalculated
for mhimum weight. The actualfrcm these proportions as
~ %Tts=—ts
,.= 0.63( 0.oQ)
= 0.0403 inch
panel Wnensims can be
——— . ... .. ..— — —-–,,
.6
= 29.5 (0.040)
= 1.18 inches
s .Ets-tS
= 35(0.064)
= 2.24 inches
end the section propetiies can be detemined from table 3 as
ii.z— tsts
. = 3.92(0.064)
= 0.251 tih
P p ts=—ts
= 6.02(0.064)
= 0.385 inoh
ti order to illustrate the use of the direct-reaiHng design chartswhen more accuracy than that correspondingto interpolationby inspectionis desired, a plot has been made (fig. 10) of the values of =f, ‘crJ
Piand H/iql given by the charts at,the design values of Pi/tS and —“
L/fi
The proporticms which @ve the highest value of Gf can be readilyselected from a plot of this kind. (For the example thesear~ so neerly the same as were obtatiedwill not be repeated.)
by inspection thatproportionsthe values
---- ... ...—..-. .— ..— —--- ______ _
-,., . ——
,
,
,
,
,
TJACATN NO. 1778 7.
As a check on the accuracy of interpolation, the ,magaitudeof %/t~
for these pro~ofiims can be detemnfned frcm table 3 smd multiplied bythe velues of tS end ?if for the desi+q. This product should be equa
to the design value of I?i. For tie eqle
iif = 30.5 ksi
z— = 1.538t~
and
= 30.5(1.538)(0.064)
= 3.0 kips per inch
. which agrees tith the design value of Pi originally assumed.
Iaugley Aeronautical MboratmyNational Adtisory Commitiee for Aeronautics
Iangley Yield, Ta., Aligust2, 1948
.
. ----- . ----- ------ ----- -— .—--- -—-. — .—-—- --.–—- .-– --— ---- --.—-—--—- ——--— ————.-
8
1.
2.
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4.
5*
NACA TN NO. 1778
REFERENCES
~, Henry L.: Design of Hat+e Plate-Stringer CmiMnations.Auto. and Aviation hd., vol. 91, no. 11, Dec. 1, 1944, Qp. 28-32and 103104.
Schuette, Even H. : Charts for the lHnhUm+eight Design of 24SJPAluminunAlloy Flat Cwrpression 2anels with Iqngitudinel Z-SectionStiffeners. NACA Rep. NO. 827, 1945.
Dow, ~OZTI?iS l?., and Hiclaam, WiUism A.: Direct+ReaUng Design Chartsfor 75s-!p Aluminum+lloy Flat Compression PUIE W* wtll~Straighi#TebY-Section Stiffeners. NACA TN No. 1640, 194-8.
Dow, Norris l?.,Hubka, Ralph E., and ROberts, William M. : Illrect-Readlng Desi~ Charts for 24-S4 A1-um+lllloy Flat CompressionPanels Having Lcmgitl@lal Straight+eb Y-Section●EWff eners.NACA m No. 1777, 1949.
,Dow, ~OZTiS F., end Hic@an, W511iam A.: Design Chsrts for Flat
Compression Psnels Ha@ng IOn@tudinal Ex&uded Y-Section Stiffenersand Comparison with Panels Having Formed =ection Stiffeners.NACA m No. 1389, 1947 ●
.
. .
‘
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TWA TN NO. 1778
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NACA TN NO. 1778
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t-
bA-
●. sI111
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fw“
Axis O&Q.,—- —.--1- .—.
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L
bw
LT--—-—
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Figure 1 - Symbols for pdhel dimensions.
. . ... .. . ... . . . ______ _____ ._ —__.. __ ___ ..__ — . ..— ——. .— -—...
.. -—- .> --- .-
20
55
50
45
40
35
30
20
40
35
P+ ksi 30
/’s
25
20
15
5560
45
40
30
4?5
15
.
NACA ~ ~0. ]
1#30”35
40
60
6
m
I I 1’1’ 1 I I I I I I I I I [1111111 I I
29— –z5-30-
35-40
-----—. -— --- __—. —--- ____ _____
/60
80:
76:
\ y f62fl.4 =E=Z3
I I I I I I I [ I I I I I I Ill 1111 I 1 I
.M 06 071M#fo ./5 .20 .# .30 .40 .60 .60
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@ure 2-0h9cf-m7L7i&&s&n ah’s for P*-T ahuniiwn-afiqy Z-stffemd pmef.. ~hi..
.778
,
.
1-+-.
.
..- —.- —.——- -.. . .,.—:., ’..;”;” -.
+-
+
TWA TN NO. f~8
5550
45
40
35
30
/?0
f6
1055
50
45
40
35
PO
1555
5045
40
35
30
15
sI I I l’]’I I I I I I Ill 1111 1111
I+W= 26?
r
----- ____
.
Flllll I +b~orS+
tdl LLllll,l n,,,, L,,ll,,l,l I I 1 I 1-
11’1’1’[
I I I I I I I I [111 11)[ I I I
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7 ,L I It +0
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I I I I, 6
,___ ---- -- . ?7.6
-i
.-
1 I 111111111 I I I I I I
I I I I46 ‘
I I I I I I I I II 1111 1111 I I I
(45)26 J?5
1 3035
/ — — 40_-— ---- -— _____
/ 50_\.
---- ---- -____, - __ 6C/ “
75:
1,ffcy=44 ksi
I I I I I I I I I I 1 II 1111 I I I I.05 .06 .07 .06.09 JO .fS .20 .25 .30
Pj— ~ hiu& G
Fiure 2-Comftied. *G5.
‘a
—. ~——. — ..- -— —..-. ____ . ______ ______
.. . . .. —..-_- ---
22 MA&A”~ NO. 1778 .
+
.656055
50
45
40
35
30
PVPtihnS for %= 0,63G
Red meensm a?hr
Hue maw a other value
.?0
I I I I
I I I I Iltll I I 1 I I 1 I I I I 1 I Ill Ill 1 I I I 3605s
50
45
— ;8
51
30
3
.
Lk#M60-- ---- ----- ,a---
30
25
k~zall I I II
~6056
‘ 50
46
40
1 I I 8 1 1 1 r 1 1 I 1 t , i t , , t , t , , , * .- , , , , , , (
I-.
~J 140-- --- ---
35t=rl
— --- -- -- ____ __80 I
’30
25
-t.I-1111111111 Ib& I 1111111111111111 I I I I I -1J?o
.05 de .07 #d9.lo J5 @ .25 .30 #o .60 .60
+?&, k~”
Fmre 3-Direct-reudhg desiq chati for 24.9T a&mLwmo/lqv Z-stWened panels. ~=0.63..
., --——— --- ———– ... —— ———.—. ,--- —--,,
;-’ . ..-.
*
NACA TN NO. 177823
+
+
606s5045
40
35
65
S5
ti
45
40
35
30
20
::6055
so
45
40
35
30
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tl’lldl I
I I I I— L-, I 753
60- ------ _ - —- -_. . ___ _____ ----\
~sfisi\ :
I > Z8 I I 164 1 I ~cy w 44 ksiI I I I I Ill 1111 1- “.05 .06 .07 .# .08 ./0 15 .20 .85 .30 .40 50 m
Fgure ‘3-camluo’ed, —: =0.63
1 ,.
——. —--—. — -——- —— ..- _______ . _. .
24
P+ ~ ksi
s
NACA TN No. 1778
~w~~80 “I&?
70
60
66
60
45
40
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