NASA NACA-TN-1050-1946 Wind-tunnel investigation of end-plate effects of horizontal tails on a vertical tail compared with available theory《和可得的理论相比 水平尾翼对垂直尾翼端板影响的风洞研究》.pdf

《NASA NACA-TN-1050-1946 Wind-tunnel investigation of end-plate effects of horizontal tails on a vertical tail compared with available theory《和可得的理论相比 水平尾翼对垂直尾翼端板影响的风洞研究》.pdf》由会员分享，可在线阅读，更多相关《NASA NACA-TN-1050-1946 Wind-tunnel investigation of end-plate effects of horizontal tails on a vertical tail compared with available theory《和可得的理论相比 水平尾翼对垂直尾翼端板影响的风洞研究》.pdf（40页珍藏版）》请在麦多课文档分享上搜索。

1、.-.,.,. 7. .0FOR AERONAUTICSTECHNICAL NOTE .:-: -No. 100 ., ,. . .OF .-.-.;JIN_L INVESTIGATION OF END-PLATE EFFECTSHORIZONTAL TAILS ON A VERTICAL TAIL .-, .-=,.- .=c1I.-. -.-in thes zpferncea.and for end-plate effects in general, F -.the”presant Investigation was dertaken. Litt and hlnge- positive w

2、hen moment tends torotate trailing edge to left.area ofvertical-tail model as defined bcmn-vention I (fig. 1) unless otherwise notedlocal chord of vertic.al-ttilmodel from leadingedge (L,E. defined in fig: 3)Ndder root-mean-square chordspan ,(recommended in refetience3) of vertic- -.= _t,. .- ,. ,Pr

3、ovided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA TN Os 1050 3Y vertical location of end plates measured upwardfrom base of vertical tail as shown in figure 1,CL sngle -of attack of vertical tail; ositive whentrailing edge.is moved to left6 rudderde

4、flection relative.to fin; positive whentrailing edge is deflected to left”AG .2 rearward of the 50-percent- bchord station ttieairfoil was modi,fiedso as to eliminatethe cuspo The plan-form ordinates of the vertfcal-tailmodel are gtven in table II.The internil balance for the rudder of the model was

5、contained in four spanwise chambers, which were separatedfromeach other at the rudder hinges. The nose and endsof the internal balance plate in each chamber were sealedto tho front o#the balance chamber and to the sides ofthe hinges with Koroseal coated voile, An enlarged cross-sectional diagram of

6、the vertical tail (fig.) sh”wsthedetails of the internal balance.Unpublished calculations based on reference 4.foran airfoil section approximately thb same as that of the model tes,d,indicated that, at a flight Reynolds numberofabolt2.0,000,”000Andwith transition at “theleadingedge,”t oundary-layer

7、thickness 6* is 0.00157C %at 0.65b. From boundary-layer measurements” it wasfound that, at values ,of_ a and. ;ale:hQj:4ascribed in referetiee 5, were appliedto the”.lift ,coeffi.cfent,rudder hinge-moment coefficient,and lm.glq,of ,attack a71 These corrections, which neglectedthe pbsence-of the end:

8、plate, were added directly to thelit% tid.”hinge-momehtcoef!ficientsand to the angle ofattack, respectively, and are as follows:AC.L= -o.olo2cAC = 3e:tbevertical-tail ,lift. .”.THEORYthq .llftof%heverttcalU.nsu:ccessfti”lA roughon .refe”ren”ce6 indicated,fairing:might possiblyas xnh aS 3.5 percent,.

9、 .- ,in whi,ct.itheroot chordsThe theory ofireference 1,of the horizontal and vertical tails are a$sumed tocoincide”.andto be thessme length.accounts for the a71.effett of,end-plate spanon the effective aspect ratio. 4.#-.a71a27a15a13 -r-.-=, IProvided by IHSNot for ResaleNo reproduction or networki

10、ng permitted without license from IHS-,-,-NACATN No,”1O5O 78a71a13of the ve.rt.icaltail., In this theory, the horizontaltail is assumed to be mounted at the bas”gof the verticaltai1a71 The minimum-induced-drag theory of reference 2accountsfol? the “vertical location of the end plates ana verticaltai

11、l that.is symmetrical about both its midspam and midchord lines, The.theory of reference 2also”accounts for the end-pla$e span but assumes.the._,end-plate.chord to be infinite. A combinatio of”H%results ,of.these two theories is shown in figure 5 Inwhich : “- =., . .,; .:.: ,.” :.-.,.,-. .,. ,-. . ,

12、.: .:,. ., ,. “:RESULTS.AiD.”bisou: -:“;”:!.,: ./. , ,.,., . ! . . . . -. - . . . . .-L:. ,-, ,F#s-ulEs”Aof“the,tbsk9,fiegiven,”ipfigures “.to 11.The tijs Zs df the data “(figs. 12 to 1.8)wis made by astud of t-eliftazi.dhinge-”momen%6;10PE$Sthrough zeroangle of attack and Wire” “zero:“rtidd-ekdflec

13、tion.,._ ._, , .“:.,“.,.I.”:, .A:“:-. . . . .1” ,! . -= _., ,“.,. ,.: ” , -, .- ,-Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-,.-t, *_ -,.:J x.- :. ;: -.-, - =- .= - .:.-,.- +_.-8 , :“-. NACA TN NO, oso “ - .Effct”of Verttcal Locatton of End Plat

14、e tThe varat”ionswith a and 6 of lift snd ruil” a zero end-plate effect at the centersectim or the vertical tall. Second, the end platesnear the base of tha vertical”tail do not produce asmuch effect as indicated by the theory, although aslightly larger effet.would be expected because of theasymmetr

15、y of the vertical-tail plan form. This seconddiscrepancy probably results from two factors: Thesupport strut probably causes the end-plate effect tocorrespond to that of.an end plate at a ventical locattonfarther from,the base of the vertical tail. Also, thestub fuselage “probably had an end-plate e

16、ffec forunpublished .$,e?tshave.indicated that a stub fuselbtit”atiition.alend=plate sbut even for this end aplate .the values of the lift parameters were just slightly -higher .t.nthose for the 2-foot-span confiPration. Acompalts of thisinvestigation of the end-plate effects of the horizontaltail o

17、n the vertical tail comparable to the theoreticalresults (for-all tee area-span conventions of figure 1.The ratio The values “inthe firs,t three ,columns ofaspect ratio indicate:thatfor this mode,lin or”dertoesttia,te CL for the end-plate-off condition from ageornet”ric,asetit?,a”tio,the formula f-o

18、rthe lift-curveslope based”oti”lifttng-,Tests “weremadeofave.rtlc.al-.tailmodel:with stubfusela ili“crobiqtionwith various simulated.horizontaltails to determine ,theeffect “ofhorizontal-tail spanand l“ation,on.the .aerodymamic charactpristios of thevertiicaltail, and the test results Were .cbmpared

19、withtheoretical ,re.s.ults?The results of.the,:ifivestigationindicated”the following conclusions: . .1.:Tne .theo?etical end-pla”teeffect i.sapproximatelycorrect “when.the.condit,io “forwh$ch it was W rived w.emet. “ “-” “ . . . .:-., ,.;?C“ThQ”n-partichl tail was i.luenced more by the locatlon ofth

20、e horizontal tai.t-“, . .r.-.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACATN NO a71 1050 1344. When the horizontal tail was located near thebase of the vertical tail, the end-plate effect wasincreased by moving the horizontal tail rearward. “:

21、Lsngley Memorial Aeronautical LaboratoryNational Advisory Cormnitteefor AeronauticsLangley Field, Vs., January 21, 1946REFERENCES1. Katzoff, S., and Mutterperl, William: The End-Plate.Effeot of a Horizontal-Tail Surface on a Verticsl-Tail Surfacet NACA TN No, 797, 1941.2. Rotta, J.: Luftkrtite am Tr

22、agfl.5 “-2e90910i“342 - .34315 oj 15 t- .03620$.561 20 -!L-56125$.; 1w 25 -4.91 3; 3; -5.2?2z5:41 “8 1 -5.414;5,49 5;:;$:?.;z- :2.995 ;p #60 a71 ;:65:$:222657; 5.638 -4-.1587; “1-3.6383.087i-3.0872.L89 -2.1898; AI. $!6 8; 8-I. 9690 1: 90 -1.279?5 95 -.66100a71 0;0 100 -.030.NATIONALADVISORYCOMMITTEE

23、FOR AERONAUTICSProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA TN No. 1050 15TALE IIPLAN-FR lNLITES OF TIC.TAIL :ODELrStations and ordinates are in incheslstation(a)-4.500-4.167-3.667-2.833-2.00-1.16701.8332.1674.6z75.500i.167.0009.16710.53312.5

24、0016.66720.833Ordinate(Forward ofrudder tinge axis)- - - - - - - - -.- -17.333- - -.- - -17.267- - - - - - -6.962- - -.-16.63616.072L1 a713171340:83;p;.58d?a71 9.733,.059.629.062.667. . AOrdinateStation(a) (Rearward ofrudde hinge axis)910121620.500.167jgs 00.167.833.1.67.617,oo.167a71 000.1679333.oo

25、.667.833.000.679333j;.000.667. 00za71 33.000.16795331 -I 2.733I 4.2945.3636.1927.067IQ. 02i8.153- - -“8.982;.;9:139.07 iiI-8.654- - -. ahleasured from fuselage center line,NATIONAL ADVISORYCOITE FOR ONAUTIC$Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS

26、-,-,-NACA TN Iioo 1050 Fig. 1.I. . .L-. .-. , .-Ama = ZOf5 q fJpQ/? =3.99ffAJpec+ Qiio=225.NATIONAL ADVISORYCOMMImEE F ASRINIAUTKS.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-1. 1.f, !,I,., ,. -.,.,!,O/?g/es d O+QCA-.,. ,., s , ,.Provided by IHSN

27、ot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA TN No. 1050 Fig. Va.-. .-8 -4 0 C9 /2Ang/e of aiock , &, deg/6 20Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA TN No. 1050 -“.-20 -/6 -/2? -8 -4 0 4 C?Pa dd

28、t?r def/ec/m d , degFigure 7. Con c/Zided .Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Fig. 8b NACA TN No. 1050.I.J4I .08$*./b)a F/.7CL .F19ure .-Cone/u ded.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from

29、 IHS-,-,-NAC,A TNR“+7C9$“.,.No. 1050 Fig. 8.I I I I I II /40r/z o/7A2/ /c0?/0/7 of end #afeq cien)$eLO.6 -.6-.4.20 HearwCOMMITTEE FORAERONAUTICS:2a. -.-.4 .0 /.2 /6 20iOPO” 02“-”a%c” jcz) deg .-fa) d=o”. .-.:2Effec) Uf horlzcwfu/ bcaflon of Phe 6 -foo /-zProvided by IHSNot for ResaleNo reproduction

30、or networking permitted without license from IHS-,-,-.NACA TN Noo 1050 Fig. 9aI.4.2.0:2NATIONAL ADvISORYCOMMITTEE FORAERONAUTICS(a) d =0 a71Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-.=NACA TN No. 1050:. . F.2!07274CLMMTTEE F AERONAUTICSfb)a=/.7

31、 c. . .“.-“. . . . .:i -:-. .-.:Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-.d.Fig. 10b,NACA TN No. 1050.-20 -/6 -/2 -8 -4 0 4 aRudder df/ecfloR d “, d9(b) a = ./.7c.FIgu Fe /0 a71 - con C/& ded .Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-