Wake surveys at the tail position of the Avro CF- 100 half model M - 0 . 6 to M ... 0.9 D. G. Gould 1952 6107A , BM49-7-9 • i, J D •• G. t.. ; ! FLIGHT lES-:ARCH WAK'S SURVEYS A'r TJE TAIL P0SI'T'ION OF '!.'!tE AVRO CF-100 Ed,1'' MOI}•:L, M : 0 1 6 to M ~ _O-L2_ D. G. G-OULD INTEHNAL A.V.ROE (CANADA) R.C.h.F. FR-lO(a) . .. ..: . . 8 22 Dec. 1952 ,, NAT 10~! AL A ERO!'J AUTI CAL ESTA BUSH M ENT N• l FR-lO(a) LABORATORY MEMORANDUM WAKE SURVEYS AT 'r.m~ TAIL POSITION OF THJ<; ' YRO CF-100 HALl MODEL. M - o.6 t o M= 0.2 &1rveys of total head losr, were made in the wake of the Avro CF-100 half model in !he Mach number ra.nr;e from M = o.6 to M = 0.9 nt nngles of attack of 0.5 • 2.5°. 4 0 50 and 6.5°. At low angles of attack at all Mach numbers. the wing-nacelle junction seamed favoura.blA in decreasing the wake width. At hip,her an~les of attnck n.nd hi#?'.h Mach numbers a peak in the waJn,i width occurred bAhind the winr,-nncelle ,tunction. The first indication of th1, wake "'ideninf: over the horizontal tail at 10·-1 anf,'les 01' attack and hif',h Mach numbers was behind the fuselage - nncelle fillet. At the hi~,her flll{'.les of attnck the wakP first spread over the tail behind the nacelle as the Mach number WRS increased. ~ NATIONAL AERONAUTICAL ESTABLISHMENT N i , FR - liJ (a) JF LABORATORY MEMORANDUM 1. I!lTRODUCTIOl! Measurement,; o•' total heafl loss were mr:tde in the wnkA of the Avro CF-100 hnlf model, at the tail plR.ne nosition, in order to determine Quali tatively neak wak<-> widths and regions of hi~h loss. A wakA ra1::e was USP.d to determine the losses and ~xtent of the wah: be hind the fusela~e, fuseln.,r:o-nacelle fillet, nacelle, win,~-nacelle junction, and two outbonrd winF'. station,. at model Mach numbers from M • n.6 to M = n.9 anri at anp;les of attack of ().5, 2.5, li.5, 6.5 clef".rees. (An::,le of nttnck •11ffi.~ !"!Oasured fro1:1 the fuselage refer1mce line). J. APPARATllS '.l'he N .11. ~;. trans rinic win -- flo~, f··,ci li ties were used. to conduct the tests. A nhoto-~ranh of tht1 wnke rakP and the hr,lf riodel is sho\-m in :?irure l. Fifty-five total head tubes, 0.nli inches I.J., werr' located in the nodel wake, and measurenents of total hAad lo s~ were made durin,c: six fli c?hts with A.n eleVPn ~:bRnnel pr"'ssnre !"ecorder. Th": nlane of th,~ leadinr: edg<' of the total hc::-cc~ tub·~s 1.~rn~ locatP.d l.'12 c aft of thf, trailin;-~ Acl,~e or the jet pipe, Le . ~~ nbout the 0.25 ~ point of the horizontal tail. 'llie ratio 0:t' inlet to eY.it .:1.re?. of the nacelle was 1._56. l~. MBTHOD A steady Mach number was est1,bli shf'd in thP, flow nnst tl":e model and. tl ·e model cycled throu[jh six cteerees in t··ro rl.egree inc!'ements, with the model pausing lfi seconds at each n.n~le. All fli,,·hts were carried 0'1t in level flir.-ht or in shallow dives so tr.':l.t ln.?: effects l.ier~ ne,:_:lir~ible. 'i.'he results a :!"0 presented in t\·.10 forrns. In Fir;t1res 3 to JO, lines of constant loss Hre plotted in r.t transvera9 nlnn,~ at the tail nosition for the four rlifferent anr:ln~ of attack OV"'r the raI11;e of Mach numbers. The wake boundary position ( ,,;, ~ o ) was estimnted from the wak, , nrafile?. nlotted for each lin"' of tubes. In Fi ·-:ures Jl to '37, 6 P. vs. vertical heicyit a;Jove Rn(, belov: the nirnlane r,~ference line 'I;-- is Plotted at six snanwise locations for the four angles of RttA.ck 11t each Mach number. NATIONAL AERONAUTICAL ESTABLISHMENT Nu. FR-lO(a) PAGL 2 LABORATORY MEMORANDUM Fi,':'.'Ures ; to 9 are contours of th,, ':m.kr at an 11.ngle of attac!c of o. 5° (relative to the ftueln.Ee reference line) for lia.c.h numbers of o.6n, 0.65, 0.71, 0.77, o.82, 0.8'..; and 0.90. Th" wa.k,:, width does not increase a,,1Jreciably 1·1ith increP-eing Mach number until M = 0.77, where the wab~ r:enerally increases. At H = o.82 tl-1.e wnke behind the fuselar:e-n".celle fillP.t spreads over the in board T}()rtion o·· the ta:.l. no n.ppreciable chanr'.'e in the wake taker, place u,~ to '.l = n, s-preads downward, :1robably due to shocks n:ppearing on the lowPr c,11 .. faces. A coinmon fen ture of all the Fi r;ures 3 to 9 i !c' a na.rro\•rinr; of thP. wake behind the wing-nacelle junction, ?L~r0,s 1 1 to 16 nre similri.r to l<,if".llres ? to 9 flXCept that thP ri.n{';le of· attack t~ incre"l.c\ed to 2.5°. The w~kP is r:enerally wider than at n.5° for thP same Bnch number. At Macr. numbers up to M = n.71. thP. w1ke behind the 1.,rinr~-nacelle junction and the win,"': widAns slir;htly with incrensin~ Mach number; the ,..,ak1 behind the n,..,.cello an6 fuselap:e-nRcelle fillet remainin<~ nssentilllly the snmc. Between M .. n. 71 and. 0. 77 the ;mb• width behind the win,,: and wing n' 'CRl le ,tunction inrreri.sas considernbl;v, and the wa.ke behind th1, fuselr,,ge- nRCfl lle fillet covl'!rs the inboard 1)Ortion of the horizontal tnil. Above M = n.77 the ,iaJ-;:, bel-cini the fuselnge-nacelle fillet remainB essentially the sa,'!P.; the •.,,.~J,:r• bel:ind the 1-rin,"'.-n{l.celle junction A.nd the win~;, ho1·rever, widens anprPCi1.Lbly. t 1;, ., • ...,_d6 the wnk':l behinr! thP nnce:1.le covers n nortion o:: thP tail at about ;;,idsnnn. At M = n.0O thic. peak ir-: ,,;one nn0 the onl,.v nortion of th·, wnke coverin • the t['.il is inbonrd near th .. fuselaee. F'if,Ures 17 to 23 are A rAp~Rt of th0 above for an an{~le of Attr:ck of h.5°. At All t-:acr, n11~bers the \•mk1e is Pt lea~t nnrtiLi:ly cov"'rin,; the } orizontal tail. At M • o.60 8.nd 0.65 thletely ntalled at M = n.60 nnd n.65, nnd ~~rtially stRllad from M = n.71 to M = 0.90 (Reference 1). 'l'her..- seems to be n TJeaL: in the vmlrn wir! th behind the •11 nt-hn.celle junction at a11 Mach numbern at this en1cJ.e of R.ttack. liP'Ur0s :1 to 17 are rlots o'' th!:! wn.k~ losses vs. vertical heir:ht for six ~r,nnwise stations. Plots 1,.re r.iPde at anp-lP.s of ntta.ck of n.,5°, 2.5°, 1~ . .5° ,.n 11.nr}e of A.tt/'lck from 2.5° to 4 • .5°. AbOVP, M - o. 77' thP wake width incr,-nses m0r 0 , or ln!'s uniforml:: with increasin," .ri.k losses 11.t !'t .o:iven Mach number r,enerally incre~se only slightly with incrensin,": 1-m':le of attr1.ct~. Fa.:- Rll :,n,~le~ o'· att.'l.ck th~ pea!: losses increase with increasin~ Mnch number. l_ NATIONAL AERONAUTIC;\L ESTABLISHMENT LABORATORY MEMORANDUM 6. CONCJ,TJSIONS Nr, PAO£:. FR-10(a) J 0 At low an,o:les of attnck (o< = 0.5 ) 1 the Wilke behind the win{"- nl'l.celle junction is nn!·rowe:r thr>.n thA w1-1.k :., behin • FIG · 2 0 4 -- --r- - 1 l - f - I I - - - ·-+-- ·-·- -+--•-- - - - +---- I - I I I I - - + - -- l 0 3 I - :-6 Rex 10 7 I I 0 2 I I .. I 0 1 5 6 7 8 9 10 MA C rl N G APPROXIMATE VARIATION OF REYNOLDS NUMBER (BASED ON c=· 1· 56 IN · ) WI TH MACH NUMBER .. FIG 3 w X -- w er f- - (/) 0::: (/) LL. ::) 0 w (/) ..J 0::: w w w -- w 0:: I- ::i;Z 0 - :, 0 I- 0 il(T (/) co ~l(T ~}T w I I l I I I I I I I I I v 0 ,, ~l(T ·7 Ft G-4 · 1 0 - a.. 1 w >- (/) a:: (/) :::> 0 (/) _J W LLl :x:: a:: <( ::> ~ (/) (/) z w 0 a:. I- a.. 0 _j ~ <( I ~ 0 .w l a:: I- lL z 0 w 0 (/) a:: 0 :::> 0 0 I- I Z lL 0 0 0 U.1 cc u.J l') - w c:r 1-- 4 4 0 N 0 0 ~z - :::> 1-- 0 i l0 - <) ~ _J w > Cl) LL 0::: Cl) w :::> 0 0::: (/) _J w w w _J ~ (/) w (/) (/) z w :::> 0 0::: LL I- a.. ~ u .....J 0 w (/) II 0 0 I- .....J I z ...... u to._ . 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F L , N f.' l Q .. "' ~ ! a 4 ,; ' (! • f- !) -t •• CF - I O O C E NT R E. - SECT t ON WA I< E SURVEY VARiATION OF TOTAL PRESSURE LOSS WITH ANGLE OF ATTACK M = 0.60 .. ·ri C) . (.A~ FIG ·3Z 0 r' ~ ::x:: I -~ u ~ I\ / I- .!v I- <:f. Y,\ If IJ... t' \ I I w 0 rl \ ~ z t I ' If w , . >-' ;1 ....) ...J ;,~ ~~ I I J ., w " ~ > 1, \ I lL z f ~ .. a:: I • w I-<1: w &, - ...J ::x:: ~ w i I ·1 I t V) :, \ ';E z 0 \ l\ I l 0 0 \r, a: ...J I I I u. --9 ! - I-\ \ I u w JI I I I w er: ~ I Cl tl> (/) :::::, t I I @ I I I (/) (/) I I I \ w w \ 0 I? \ a: a: I I 1 I I-I I t> Cl. I l \ I z \ I w i I I I \ u ...J . \ I \ \ I \ \ z 0 I-0 n :.,. \ I I \ I I ,. 0 I I \ 1 u \ I l 0 ilcr 0 ,:;I 0 ~lu 0 0 0 ~lcr 0 0 ~ICY 0 0 0 • cr 0 01 - ..J w /' > (!) . 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Wake Surveys at the Tail Position of the Avro CF-100 Half Model at Mach 0.6 to Mach 0.9

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AVRO Museum

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Web Links and URLs

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Note