ccnt,rred nt, (m -1- 1, n). 1'110 two t,xptwsions are t.hertwpon cornt)ined in such a way thnt ternls of ortlcr Aq2 are elitnina1.rtl. The corrcsponclir~g difference qnot,icnks can I,c given the, form (index we 1 I omitted) : a',, 1 { I I I 2 T I I 1 7 I] I 0 ( A . 1 ) (9 69) il,l 2 /I 11,' where p1 - 1 l2 (I -+- K), rPz - L ~, .-- 2 r1 J'~, I>,, -= I . Eq~tn.tions (9.69) nncl (9.70) rcrlr~cc t.o t,hc st.nntlartl form for cent,ral difl'crenccs when K = I. For the (-tlcrivnt,ivrs in cqnnt.inn (9.64) a simple bnclrwnrtl tlini.rrner formule is used y - Fsr 11. n -- Fnr, n E - -I om. (9.7 I ) At -- The 1nrgc.r I,rtlnc.at,ion error which appcn.t,s here is balancctl by t,hc it.crat.ivc scltclne proposc(1 for solving thr tlilkrcncc c-qt~at,ion. 'l'llc non-lincn.r t,ernis in r(lnnt,ion (9.04) Imvc to be rcplaced by lincarizccl diflkrencc quoticnt.s. Tho tcrlns fFIl and FFg may serve as exntnples and thcy are writ,t,cn as l'hc lincnrizrtl Iini1,r-clifl'ercnw qnotionts given nhove are su11st~it.ut~erl into the tlifl'crentinl ty~tnt.ion (9.G4) nnd Lhe result is multiplied througlt by A E to give n tlilYcrcnce equa.t,iotl. 'J'his is writden ns follows i. The n~ctl~otl of finite dilTwcnces 191 111 cqun1,ions (9.75), 6 and 0 nre cvnlunlctl nt (111. 1- I), mtl ot~ly the vn.rir~l,lcx wit.11 sttp(wcripll i ntt 11~1cInlc~1 through st~cccssivt: it,crntions. To s~~xxl-III) t,Itv il~r~~:t,l,ion proces.s t,he tcrrns (/S)t can be licJ)t constnrlt. (equnl to t . 1 ~ &luc nt t.hc prrvious shtion) unt,il initial convergence is nchicved. Method of nolution: Equations (9.74) rcprc~ont~ n ~ oof t N-1 si~ntlll.nncwus r~.lgc:- I~rnic equntionrr for the unlrnown k;ntl,n (n = 2, 3, . . ., N). At, cnch levcl IL t.l~rcc unknown quantities nppenr, namely Fnajl, .-I, Fm.kl,n and Fniit, ,,+I, but sincc F,+I,~ and Fm+l,~ nre known from the bonndnry conilitions, 1.11~ totnl nurnbcr of cquntions equals the nunlber of unlrnowns. The set of nlgclmic cqunt,ions rnn be writt.cn in so-callod tllrcc-tlingonnl matrix form. MnLriccs of Illis ttypcwhcro oK-tlir~go~tnl elements vnnish outdc the three-tlingonal band can bc inverted bg n sirnplc: and direct nlothod well suit.cd for digital con~putcrs.l'o end tlriseqna.tion (0.74) is rcwrit,toll in "stantlard form" (subscripts (m -1 I) ornittcd) Thc botlnclary conditions arc F1 = 0 nntl PN = 1, (9.70) wllere IL = I tlenotcs tbc wall and ?t = N thc edge of the bountlary Inycr. J1, is asst~tn- etl now t,llat a solution existst in tllc form The boundary condit,ion F1 = 0 nnd t,he rcyuirernent t,llnt rquation (9.77) sl~ould rcrnnin valid indcpcntlcnt,ly of the sl,cp size /Iq leads to A direct, colisrquencc of rqnntion (9.77) is that When the preceding expressions are substitutml int20 oqn. (!).741,), 1.11~ following relohion is obt.aincd By tncnns of equalion (9.81) and the condition (9.78), it becomes possil~lc t.o cotnpot,~
192 JX. 1Cxact sol~tLion~ of tho stmdy-state l~ountlary-layer equat,iona i. Tho method of finite diffcfcrrnoes 103 R, and G',, for sucoessive values of n startling wit,h ?z = 2 for all grid point,s between the wall and the edge of the 1)onndary layer. Sinco 17,,.,l for 12 = N-1 is known from rqnat,ion (!).70), it lmx~mcs possible to evaluate all nnlznowns F, by means of equation (9.77) whilc t,mversing td~o boundary layer from t,ho edge t,o t,he wall tJlrongll (Icrreasing va111cs of n, i. c. for 17. -- N-l , N--2, . . ., 2. '1'11is cornplr1,rs lhr cdc1lln1,ion of Il',, (7.- F,, ll.n) in ono it.c~.nl,ion. On(:(: I{',,,, 1111s I)c~w tlr~r~~nii~~r(l. thr cot.~.c.sj)ondi~ig solntion for /0141,n ca.n be found by rlireot. nun~wirnl inhcgrxt,ion of equat'ion (9.05). The t,rapezoidal rule snfficcs for t,his purpose. The calculat.et1 vniues P7n4.1,n a.nd /,,+l,. are used t,o dntmnline new and improved ,. valrtcs of t,he coc,fficients A,,, I?,,, C,, which in t,urn leads t,o new and improved values of F,+I,,, antl f,, , I,,. 111~ ~WOCCSS is t.~rmin:~tcd when t,hc rcsnlt,~ of two s~~cccssivc it,rrnt,ions ngrco t,o within a specified tdcrancc, typically of order 10-5. 'l'ho convergrnce is nsnallp rapid, t01ree t,o four iterations being adequate in most cases with st,rp sizrs A.r in l,he range 0.01 t,o 0.05. In crrt,t~in pro11lc:nis it, I~ecomrs n~ccssnr~ t,o nllow for bonnda.ry-li~y(~ growt,l~ 1)y inrrc,asing N (or ve) as t,hr calcnlatrions proceed tlownst,reant. The houndarylayer edge is rlcfinctl by thr rcquircmcnt t,hat tho difference FN-Fnr~l should be Iws t,lian a sprrificd value, t,.vpically of ordrr 10-4. 7'hc growth, in t,crrns of the presrnt variablcs, is usually very modest even for cases involving separation. A vnrial~lc of primary intcrcst. in the calcnlat,ion is the s1.rrs.s at t,hc wall; it,s vnluo can bc tl~t~erminetl with good accuracy from the five point formula Iuirinl vnlr~cs: \Vlic~n using hnl111lrr1.c.tl similar solrrl.ions as s1,arling vdrlcs, ext,c:nsivc int~c~t,j)olat,ioti is rcclnirecl whrncver variable step sizes Ay,, are nsctl. It is rnorcx convcnirnt, antl efficient also t,tr gcnerate t,hc sin~ilarit~y solut.ion by finite tlifi~rr-rcs t.hroupl1 surcrssivc iterat,ions. The equat,ion t>o be solved is oht,aincd from cclna,li~m (!).64). and can I)c writtam in 1inoar.ized form as guessing a so la ti or^ which salisfics the boundary condit,ions), whereas those wit,ll index i arc to be found in the 1:-th or cnrrcnt itcmt,ion. 'L'lte tlifTcrc:nc:c quol,irnf,s (9.69) and (0.70) are now snl)stitut,cd ink) equa0ion (!).84). 'I'hc rrsult. is a tlilli~~~~ncc equat,ion which can be writt,en in the standard form of eqnat,ion (9.74), with coeffi - A linear variation in F suffices as an initid guess, Fo, and the corrcspontling value off is detmmincd from equation (9.86). The coefficients A,, /I,,, C,, and I),, nro (XIoulntcd next, and tltc corresponcling vnlncs of /?,, and (r,, arc tlct~errninctl ~~eross thtbonntlary layer. The recurrence rclnlion (9.77) and t,he bountlnrg contlit,iorls (!).78) are then used to determine the new it,crat.e, FI, across thr bounclnry lager. 'Yhr process is repeated until the difference bct,wcen successive it,eratrs becomes smaller than the specified t,olerance. The number of it.emtions required is typically of order 8 to 12. The method is simpler t,llan t,he usl~al W~ooting'' ~ncthod used for two-point lmnntlary-vnlnc problem$ arid it converges in many rases WIICIT t,lrc In,t.ter mct,l~otl fails, for inst,ance for very large blowing mt.cs. Applications: The finite-difference method prescnt.ctl hrrc is in1,cntlctl as n prnctical engineering t,ool. Great,rr accuracy cnn be achicvcrl with a more clalwrntr procedure, 1,111, t,his in turn leads t,o greater cotnplexit,y in fornlnlat,ion mtl progrnmrning and to an increased demnlid for computm t,ime and cnpacit.y. The conipnting time nnd accnmey tlrpcnd for all tlifTcrcncc ntet,lrotls on the skp sizr nsrtl in thr rnlrw Iations. It, is of int.crest, to exa,mine the accuracy of the present, mct,hotl in a few cases for which very accurat3e solut,ions are known. The cases considrretl are 11owa1~t.h'~ linrnrly retarded flow (cf. Scc. IXd) a,nd the circular cylinder with a pressure clistrihut.ion ncrortling 1,o pot.cnt,inl 1.hrory and nccotding t,o t.hc cspcriments of I[ic.n~r~lz (c/. See. X c). '1'11~ rrsult,s for n "normnl" step sizc and a "srnnll" step size arc tabnlntcd 11clow. lhtn t.11~ C:IICIII:L~~ rcs1111~s only the locat.ion of the scl~n.rt~.l.ion 11oin1s IIII! sl~own. Case ('o~kIerrd 1 Present redts 1Sxnct 1,inenrly set.artlrtl Ilow Circular ryli~~tlcr (l'okntinl flow) -. Circular cylit)tlrr (Ilic~ncne prms. tlntn) I (1) x,' = 0.1227 (2) x,* = 0.1210 (1) 4, = 106.13" (2) 4, = 105.01 O r8* = 0.1 I!)!) (Ilownrtli) or r,* = 0.1 198 (l,eig11)[44] I or T,* - 0.1203 (Sc4~ortinr~~) 4a - 104.5' (Srl~ocnni~er) (rf. Scc. Xc) -- (I) $, = 80.98" (2) 4, = 80.08" #. -= 80WC (.lnlli: nnd Stnitl1)(.42/ (interl)olntrd) .-
- Page 1 and 2:
McGRAW-I4ILL SERIES IN MECHANICAL E
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vi Contents CIIAPTEII V. Exnct ~olu
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Y Contents A " I XI X 'I'lirorrt.ir
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xvi I'orcworcI Thc result was t.11~
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From Author's Preface to the First
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the aid of thorctical considcmtioti
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even in fluitls wit,lt vcry srnall
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10 I. Or~llinr of lluicl rnot,ion w
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The vclwil y IL at some point i11 t
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Fig. 1.6. Firld of flow of oil nho~
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22 I. Outliric of fluid motion with
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2 (i TI. O~~tlittr of Imun~lnry-lsy
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Fie. 2.511 Fig. 2 .5~ Fig. 2.5b Fig
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S - point orscpnrnt.ion T'ig. 2.12.
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3 8 \ Y?\ If. 011tli11e of boundary
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42 11. 011tli11e of Iw~~ntlnry-Inyr
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[:j2a] I?o~cilhrntl, I,.: Thr forn~
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50 111. l)crivnt,ion of thc cquntio
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Fig. 3.3. Tmcd clintor1,ion of flui
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of flltitl is strcsscd in thrcc nlu
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1:i~ 3.8. Qltnsintzt.ia cotnprrssio
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66 111. 1)wivntion of the eqnntions
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CHAPTER I V General properties of t
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74 TV. Gencrol proprtic~ of tho Nov
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Ilcre v, c, :tntl k tlrnol,c 1.I1t:
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conclil.ion (4.14) plays n part wl~
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86 V. 1':xact solul ions of tlir N:
- Page 56 and 57: 90 V. ICxnct sol~ttion~ of tho Nnvi
- Page 58 and 59: 94 V. Exnct sohltiono ol' tho Nnvic
- Page 60 and 61: Table 5.1. Functions occrtrring in
- Page 62 and 63: 11. Flow taenr n rotnting disk. A f
- Page 64 and 65: 106 V. JCxact solutions of the Navi
- Page 66 and 67: cnu bo npplirtl nt mont, nn fnr RS
- Page 68 and 69: 114 VI. Vcry slow motion where r2 =
- Page 70 and 71: 1 I8 VT. Very slow motion r. 'l'l~o
- Page 72 and 73: 122 VI. Very rrlow motion ext.endcd
- Page 74 and 75: 126 VT. \'cry slow rnot.ion Part B.
- Page 76 and 77: 130 VII. Boundnry-layor cquntionzl
- Page 78 and 79: '1. Skin friction \VlIat1 t.11~ I)o
- Page 80 and 81: 138 VII. no~~ndnry-layer cqnntions
- Page 82 and 83: 142 VII. Hor~nclnry-lnyrr rq~~ntii~
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- Page 86 and 87: CIIAFTER VIII Gencral propertiee of
- Page 88 and 89: 164 VIII. Ccnernl propertic8 of Lhe
- Page 90 and 91: 158 VIII. General ppropcrtics of th
- Page 92 and 93: VIII. General propertien of the bou
- Page 94 and 95: 'I'his c.quat,ion Lmnsforms into t1
- Page 96 and 97: 170 TX. 1Sxact uolutions of t.ho st
- Page 98 and 99: 174 TX. Exnct ~olut,ionu of tho sto
- Page 100 and 101: 178 IX, Exact solutions of tlrc ste
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- Page 104 and 105: 1 86 10 0.8 0.6 0.4 0.2 0 -0.2 -0.4
- Page 108 and 109: 194 IX. Jqxnct eolutions of thc stc
- Page 110 and 111: O~l:cr ehnpw: Second-order cITcetls
- Page 112 and 113: 202 X. Approximate rncl.hoda for st
- Page 114 and 115: 206 X. Approxitnnte rnct.l~otls for
- Page 116 and 117: 210 X. Approximate mcthod~ for shad
- Page 118 and 119: 214 X. Approximato mothotls for sha
- Page 120 and 121: 218 X. Approximntn met,hods for shn
- Page 122 and 123: 222 X. Approximate methods for stea
- Page 124 and 125: 220 XI. Axinlly symniobricnl nnd th
- Page 126 and 127: 230 XI. Axinlly symmctricnl and thr
- Page 128 and 129: 23.1- XI. Axially uynimet.rira1 nnc
- Page 130 and 131: the two wries expnnsicws for sin (%
- Page 132 and 133: 242 XI. Axially nymmct.riral and tl
- Page 134 and 135: in cross-flow, tlrprntls only on lh
- Page 136 and 137: 250 XI. Axinlly nyrnmet,rirnl nntl
- Page 138 and 139: XI. Axinlly ~,vn~n~et.rir;~l nnrl I
- Page 140 and 141: 258 XI. AxhIly syn~rnrtrirnl nncl t
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- Page 144 and 145: 206 XIT. l'l~rr~nnl bo1111r11iry ln
- Page 146 and 147: 270 XIT. 'I'l~rrtnal boundary layer
- Page 148 and 149: can I)r rct.ni~rrvl in inrotnl~rrss
- Page 150 and 151: if wc: pillf - - 'I1, - (A7'),. 11,
- Page 152 and 153: Rotntirig rli~k: (:II:I~I. V, in pn
- Page 154 and 155: 286 X11. 'IY~rrrr~al bo~~ndnry laye
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290 XlI. Tl~rrnmal boundary layers
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with 0,' -. () at, r] - 0 and 0, =
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2!)H XI[. Thcrn~al bor~nrlnry Inyrr
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302 XJI. Therninl boundary layers i
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306 XII. Tllcrrnal hor~ndary layers
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310 XJI. 'I'hcrmnl boundnry layers
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314 X11. Thermal boundary laycrs in
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318 XIT. Tl~crnial bonndnry layers
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322 XII. Tl~or~nnl I)onndnry lnyers
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326 X l I. 'l'l~crn~nl hounrlnry ln
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330 X[[1. lmninar bor~ndnry lnyers
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334 XIIT. Lnrninnr 1)oundary laycra
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338 XI I I. Im~linnr I>orirtclt~ry
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342 XI11. Tmninnr Imlndary layeru i
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346 XI 11. T,ntninar I~or~nrjary hy
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350 XIII. 1,mninnr honnclxry lnycrn
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354 XI 11. 1,nminnr h~nrlnry 1:ryrm
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Fig.. l3.16. In 13.18. lain~innr ho
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a Intninn.r l)out~rlary I:~.ycr, bu
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1 I Itc vnriolts c4Twl.s ol'sl~oclt
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370 XIIJ. I~tminar boundary layers
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\'all I)rirst., 15.11..: 'l'hr prol
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CIIAPTER XIV Boundary-layer control
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5. J'rrvrntion of trauaitinn by the
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frorii th; 1c;ulitig rxlge! (l3l:wi
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390 XIV. Ilo~~n~lnry-lnycr contml F
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. - v, (x) =cons/ Fig. 14.14. 1,ant
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invc?st.igai.ctl. In this msc too,
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402 XIV. Dounclery-layer control 1.
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Ni\('A 'rM !I74 (1!)41). 1861 Sinli
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110 XV. Non-~teldy bortndnry layers
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414 XV. Non-st.cncly hour~tlnry Iny
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418 XV. Non-slmrly l~orrnclnry Inyr
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422 XV. Non-st,cndy hoixnd~ry Inycr
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420 XV. Non-nl,mdy Fig. 15.58 Fig.
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XV. Non-utcncly boouclary lnyers wh
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434 XV. Non-stcxcly boundary layers
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438 XV. Non-atcndy boundnry inyer~
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442 XV. Norl-st,aady boundary Isycr
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440 XV. Non-st,rndy ho~~nclnry laye
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450 XVI. Origin of tnrhulence I pyi
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XVT. Origin of turbulcncc I n. Some
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458 XVI. Origin of turbulence I b.
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462 XVI. Origin of tnrb~rlmcc 1 num
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466 XVi. Origin of t.r~rhr~lrncc 1
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470 XVI. Origin of h~rlwlcnce T I R
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474 XVI. Origin of l,t~rl~~tlct~rr
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478 XVI. Origin of I.rtrb~tlmcr 1 t
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482 XVT. Origin of tmbulcncc I c. E
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486 XVI. Origin of k~rbulenre I 148
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490 XVII. Origin ol t,urbulencc 11
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404 XVII. Oriein of tnrbnlencc TI F
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498 XVII. Origin of turbnlmco II t,
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Tlw tlisl.nr~cc Iwt,wccn the point,
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c. Efict of ~urtintl on trnt~nition
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510 XVl I. Origin of Idmlrnro I I '
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514 , XVII. Origin of turbulence 11
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518 XVI I. Origin of turhr~lcncc 11
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on the bnsis of t.hc tl~corct,ical
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626 XVII. Origin oI t.11r011lonco I
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630 XVII. Origin ot t.~~rhr~lrncc J
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XVII. Origin of t.urh~~lencc TI 7 !
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638 XVII. Origin of t~~~rbnlc~~rr I
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\vi(,l~ a (-ylit~(lw envcrv(1 wiI.1
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646 XVII. Origin of turbulence TI F
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550 X\'ll. Origin of t,11rh111rnrc
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554 XVII. Origin of t,rlrbuloncc TI
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558 XVITI. Fundamentals of tr~rbule
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562 XVlI1. R~nclnmont.nIu of tur1)u
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The corrrlnt,ion co~ffiricnt~ y~ ra
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670 XV111. I'nntlntnrt~t~nlrr of tt
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574 XVIII. 1'undnnient.alu of tnrl~
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CHAPTER XIX Theoretical assumptions
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682 XIX. Thcoroticnl wsltmptionu fo
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586 XIX. Throretical aaotin~ptiona
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5l)O XIX. Tl~rorrt,icnl nmumptions
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594 XIX. 'rheoreticnl nssornptions
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698 XX. 'I'~~rl~ulrnt flow f,lrro~~
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602 XX. T~rrbulcnt flow thro~tgh pi
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606 XX. 'l't~rhl~lc~rit flow thro~~
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GI0 XX. Turbulent flow throngh pip
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Icror~~ ()I(, phj.sic*:~l ~)oint. o
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620 XX. Tnrbnlcnt flow tlvough pipe
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dimensions Fig. 20.26. 1tc.sist.anc
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628 XX. T~lrbnlmt flow through pipe
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632 XX. Turhulcnt flow through pipc
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636 XXI. Td~nlcnt houndnry layers a
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610 XXI. Ttrrbulent bor~ndnry layer
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644 XXI. Turbulent boundary laycrs
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048 XXI. Turbulent boundary layers
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652 XXI. Turt)~~lcnt houndnry layer
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656 XXI. Turbulent boundnry layers
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660 XX I. Tl~rhlent bo~~ndary layer
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664 XXI. Turbulent boundary layers
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CHAPTER XXII The incompreesible tur
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672 XXll. 'l'llc incon~prcssiblc tu
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070 XXII. Tlic incompreaaibto lnrl)
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FRO XXII. Tho incornprcs~iblo turbu
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684 XXII. 'Yhc incon~prcssible Lnrb
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688 XXJI. The incon~prcssible t,urb
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002 XXI1. Tho inro~nprc~sil~lo tt~r
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is prol)nt~t,iot~nl to the rnclius.
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lf$8] Mucsm:tnn, 11.: Z~~snrntncnhn
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70-t XX I1 I. 'Ihrbulcnt bonrwlnry
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708 XXIII. Turbulent bonndnry Iaycr
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712 XXI 11. 'I'~~rl~~~lemt bo~~ntln
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716 XXIII. 'I'urbr~lcnt bor~ntlnry
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720 XXIII. Turbulent boundary layer
- Page 373 and 374:
724 XXlll. 'rur1)ulcnt boundnry Iny
- Page 375 and 376:
[04] Smith, P.D.: An integral predi
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732 XXIV. Frcc trtrbt~lent flows; j
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700 XXIV. Prrc tr~rb~tlent flowa; j
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Neglecting u12, we obtain XXIV. Prc
- Page 383 and 384:
744 XXIV. lhc L~trl)ulcnt Ilow~; jo
- Page 385 and 386:
748 XXIV. Free turbulent flowa; jet
- Page 387 and 388:
762 XXIV. Frcc td)ulcnt flows; jcta
- Page 389 and 390:
756 XXIV. Prrc torbulent flows; jet
- Page 391 and 392:
760 XXV. DotcrminnLion of profilo d
- Page 393 and 394:
764 XXV. I)ot.crtninntiotl of profi
- Page 395 and 396:
768 XXV. Determination of profile d
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XXV. 1)obrlninalion of proRlo drag
- Page 399 and 400:
776 XXV. 1)ctormination of profile
- Page 401 and 402:
A. Reviews organized in serial publ
- Page 403 and 404:
784 Bibliography Sherman, I?. S., I
- Page 405 and 406:
Clementa, lt.R., and Mad, D.J.: The
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Oswatitach, I
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H:I:IR, 11. 776, 777 Ilnnsr. 1). 62
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List of most commonly used synibola