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AAIA - 2001 - 2407 STELGNI WELPITLU MHTI WGNI WAF OSISYLAN AECNAMROFREP M. J. Smith •, N. Komerath +, R. Ames › , O. Wong › , Scho ol of Aer ospace Engineering, Georgia Institute of Technology, Atlanta, Georgia and J. Pearson ** Star Technology and Research, Inc., Mount Pleasant, South Carolina TCARTSBA found that the pin feathers worked to reduce drag gnirud gnidilg ,thgilf sa llew sa gnieb desu o t This effort examined the potential of multi - stelgniw provide roll control, in the same manner as rof eht noitcuder fo decudni gard t uohtiw snoreliano aircraft. T hese multi - stel genri awetiuq increasing the span of aircraft wings. dnWil ennut netfo gnol dna ,tnenimorp sa nieht case of the models were constructed using a NACA 0012 .rodnoC ainrofilaC liofria noitces rof eht ,detsiwtnu ralugnatcerg niw nredoM tseretni ni stelgniw snaps eht tsal 5 2 dna talf setalp rof eht iw nglets. Testing of the .sraey drahciR Whitcomb of NASA Langley snoitarugifnoc derrucco revo a egnar fos dlonyeR Research Center first looked at modern numbers from 161,000 to 300,000. dnWil ennut snoitacilppa fo stelgniw otnart sport aircraft in the balances provided lift and drag measurements, .s0791 eH desu ,llams ylraen lacitrev snif dellatsni dna resal wolf noitazilausiv deniatbo pitgniwx etrov no a CK - A531 dna thgilf detset 1 ,2 ni 9791 d na information. The Cobalt unstructured r evlos .0891 ehT telgniw tpecnoc yllautca setad kcabo t 06 generated flow simulations of the experimental a tnetap ni ,7981 tub ton litnu Whitcomb noitarugifnoc aiv noitulos fo eht reluE snoitauqef o detagitsevni telgniw scimanydorea did ehtc tpecno motion. The results show that certain multi - telgniw mature. Whitcomb showed that winglets could snoitarugifnoc decuder eht gniw decudni gardd na increase an aircraft's range by as much as seven devorpmi D/L yb 51 - 30% compared with the percent at cruise speeds. A NASA contract 3 ni eht ilesab en 2100 .gniw A laitnatsbus esaercni nit fil s0891 dessessa stelgniw dna rehtogard - noitcuder evruc epol ssrucco ht ilward edhaiedrps fo stelgniw ,secived dna yeht dnuof taht pitgniw s ecived tes ta orez ecnedicni evitaler ot eht .gniwl ardehiD ,stelgniw( feathers, sails, etc.) can improve drag - spread also distributes the tip vortex. These eud - ot - tfil ycneiciffe yb 01 ot %51 fi yeht e ra observations supplement previous results on drag dengised sa na largetni trap fo eht .gniw sAdda - noitcuder d eu ot tfil noitatneiroer htiw d etsiwt no ,secived ,revewoh yeht evah neeb nwohs ote b .ecnedicni evitagen ta tes stelgniw detroivmepetrewnoarit lftnalohgl re. mo afn ce INTRODUCTION nalI oorK tela 4 aed tl htiw eht daorb tpecnocf o non - ranalp ,sgniw hcihw sedulcni .stelgniw y ehT nI eht ,s0791 stsigoloib nageb ot kool ta ehtg niylf deweiver a yteirav fo tfarcria ,sepyt g nidulcni characteristics of soaring birds such as eagles, ,stelgniw gnir ,sgniw xob ,sgniw dna e ht ,skwah ,srodnoc ,serutluv dna .syerpso hcaEf o noitatiolpxe fonon - ranalp sekaw ni .lareneg h cuS these birds has h hgi tfil sgniw htiw ”nip“ srehtaef ta designs are of interest because of the ril aitnetop stsigoloiB .spitgniw dettols ecudorp taht sdne eht ro fr exweot l rd goeta vsur,aodnehartpcisnwi a yek constraint for many aircraft. However, their effects no ytilibats dna ,lortnoc scitsiretcarahc fo e kaw vortices, and structural implications of non - ranalp • .AAIA wolleF etaicossA ,rosseforP tnatsissA desiganarsle is mop ortant. + orP .AAIA ,wolleF etaicossA ,rossef › AIARGAMserAeSssamtiedbusauedtrareact nnhett , The Wr thgi srehtorb detiolpxe eht l arutcurts › AIARGAMserAeSssamtiedbusauedtrareact nnhett , segatnavda fo .senalpib tA yrev wol s dlonyeR ** AAIA wolleF etaicossA ,tnediserP numbers, highly cambered, thin sections perform thgirypoC (cid:211) 2001 .htaremoK .N dna htimS .J .M yb better than thicker sections, making the cable - scituanoreA fo etutitsnI naciremA eht yb dehsilbuP braced Wright biplane concepts especially permission.with Inc. Astronautics, and 1 AmericIanns titAuoetfre o nautiaAcnssdt ronautics Report Documentation Page Form Approved OMB No. 0704-0188 Public reporting burden for the collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden, to Washington Headquarters Services, Directorate for Information Operations and Reports, 1215 Jefferson Davis Highway, Suite 1204, Arlington VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to a penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number. 1. REPORT DATE 3. DATES COVERED 2001 2. REPORT TYPE 00-00-2001 to 00-00-2001 4. TITLE AND SUBTITLE 5a. CONTRACT NUMBER Performance Analysis of a Wing with Multiple Winglets 5b. GRANT NUMBER 5c. PROGRAM ELEMENT NUMBER 6. AUTHOR(S) 5d. PROJECT NUMBER 5e. TASK NUMBER 5f. WORK UNIT NUMBER 7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) 8. PERFORMING ORGANIZATION Star Inc,Star Technology and Research Inc,3213 Carmel Bay Drive Suite REPORT NUMBER 200,Mount Pleasant,CA,29466-8513 9. SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES) 10. SPONSOR/MONITOR’S ACRONYM(S) 11. SPONSOR/MONITOR’S REPORT NUMBER(S) 12. DISTRIBUTION/AVAILABILITY STATEMENT Approved for public release; distribution unlimited 13. SUPPLEMENTARY NOTES The original document contains color images. 14. ABSTRACT see report 15. SUBJECT TERMS 16. SECURITY CLASSIFICATION OF: 17. LIMITATION OF 18. NUMBER 19a. NAME OF ABSTRACT OF PAGES RESPONSIBLE PERSON a. REPORT b. ABSTRACT c. THIS PAGE 10 unclassified unclassified unclassified Standard Form 298 (Rev. 8-98) Prescribed by ANSI Std Z39-18 .evitcartta ,revewoH llaG dna timS h 5 detartsnomed taht eht noitidda fo elgniss telgniw Robert Jones 41 debircsed eht segatnavda fo elgnis otno eht senalpib dedda a %31 tnemevorpmin i stelgniw rof llams ,stropsnart no hcihw yehtn ac ,ecnarudne sa llew sa gnisaercni eht tfil - curve edivorp %01 noitcuder ni decudni gardd erapmoc slope and the maximum lift coefficient of the htiw lacitpille .sgniw stelgnWi era won g nieb .elcihev incorporated into most new transp ,strog nidulcni the Gulfstream III and IV business jets 51 , e ht nI tnecer ,sraey lareves sepyt fo p itgniw gnieoB747 - 004 dna llennoDcM salguoDDM - 11 improvements evah neeb .detnetap ehT” diorips“ ,srenilria dna eht llennoDcM salguoDC - 71y ratilim gniwpit 6 secudorp a noitcuder ni decudni, gard transport. hcum ekil taht a .telgniw hguohtlA a desolcg nitfil metsys yam etanimile eht gniw ,spit ti seodt on stelgnWi nac osla eb deilppa ot c imanydordyh .ekaw xetrov gniliart eht etanimile surfaces. Examples include the America's puC taoblias sleek htiw ”,stelgniw“ sa dezilitu ybe ht ,nilhuR ,aitahB dna ajaragaN 7 deton taht e ht 3891 s’aciremA puC renniw ailartsuA“”.II 61 The noitidda fo a telgniw yllaitnatsbus decuder e ht decudni gard fo anon - ranalp metsys nac ebr ewol rettulf deeps fo eht gniw ta cinosnart h caM than that of a planar system of the same lift and numbers. In addition, the effect of sideslip 8 n o .naps sihT si eurt neve nehw eht gniws ecafrus stelgniw si ot ecudorp desaercni sdaols uogolana themsel ves are co - ,ranalp tub rieht xetrovs ekaw ot gniw sdaol desuac yb elgna fo .kcatta nartaS 9 are not. The keel and rudder (or twin keel sevni detagit eht citats dna cimanyd ytilibatsd na surfaces) are coplanar, but due to the substantial control and free - thgilf roivaheb fo a 63.0 - scale yaweel elgna dna lanidutignol tnemecalpsid foe ht model of a canard general - noitaiva enalpria htiwa two surfaces, the wake downstream of the boat elgnis reh srueplleporp dna stelgniw ni eht yelgnaL resembles that of a bip enal ,metsys dna e ht 03 - yb06 - tooFWind Tunnel. He found the model .yllaitnatsbus decuder si gard decudni ot tibihxe yrev elbats lardehid tceffe tub k aew .ytilibats lanoitcerid Imamura 71 te .la dezylana eht noitacilppa f o . sd en ynueio hb fdTrlnuaitnwoitn es vtonetolcgniw ehT dednelbtelgniw 01 secuder gard ybg nitanimile taht a llams telgniw noitallatsni elgna sesuaca eht ytiunitnocsid neewteb eht gniw pit dna e ht large increase in the power coefficient but a sma ll .telgniw A dehtooms noisrev si desu no ehty ltneg increasietn h fel atwisbee ndinmgo mencto mpared tpewspu telgniw fo eht gnieoB737 - .004g nieoB htiw eht sedalb htiw yllaidar dednetxe . stelgniw B ssenisu steJ dna noitaivA ,srentraP .cnI e vah grebnehceR 81 describes a concentrator principle embarked upon a cooperative program to market rof dniw ,senibrut hcihw si desu yb sdrib htiwt ilps lanoitnevnoc stelgniw rof tiforter ot eht gnieoBx x7 gniw .sdne ehT gniw pit secitrov esuac eht wolf ot seires fo .sreniltej thgilF stset no eht g nieoB ac ,etarelec hcihw srewol eht decudni .gard e H Business Jet 737 - 004 detluser ni a %7 g ard deilppa eht tpecnoc ot etaerc a dniw“ ”snel n i reduction. Theoreti lac snoitciderp dahd etacidni hcihw elpitlum hgih tfil sgniw era degnarra otm rof taht eht noitarugifnoc dluow evah ylno a 1 - 2% a ralucric naf tuoba a dniw .enibrut ehT dniw rotor ,tnemevorpmi dna dniw lennut stset dahn wohs in the center experienced a maximum power ylno %2 gardnoitcuder 11 . sihT setacidni tahtd niw augmentationf act oro fm oret han8 . lennut tset stluser fo telgniw snoitarugifnocd luohs .noituac emos htiw deweiver eb erehT sah neeb detimil noitagitsevni foe lpitlum winglets for aircraft. The split - pintgised 91 znie Hy b ehT tsrif yrtsudni noitacilppa fo eht telgniw tpecnoc gulK rof na tfarcria gniw nac eb deredisnoc a saw ni .senalplias gnilloC 21 sevig na t nellecxe evitimirp elpitlum .telgniw tI saw detaerc ott iolpxe weiver fo stelgniw rof senalplias taht e h eht non - ranalp ekaw yrtemoeg yb g nicuder detag intisev neih tsa xyet TiM s&0rA1exv 7itnoUof decudni gard dna gniw .sserts stsigoloiBe vah woL - deepS dnWi lennuT gnisu alluf - scale model enod evisnetxe noitagitsevni fo eht tilps spitgniw fo of the outboar d 5.6 feet of a 15 - meter - class high gniraos ,sdrib hcihw era dnuof ot eb y lhgih performance sailplane wing. Marchman, Manor, effective. Vance Tucker, a biologist with an dnayreaF 31 dnuof taht cirtemmys stelgniwe rew aerodynamics background, demonstrated that the tseb rof lareneg noitaiva ,tfarcria tub erew s sel pittols s of soaring birds reduce induced drag and effective on tapered wings. Their tests also increase the span factor of the wings 02 . He found dewohs a noitcuder ni gniw ekaw turbulence from remarkable improvements of slotted wingtips .stelgniw eht derapmoc htiw lanoitnevnoc sgniw htiw a kralCY 2 AmericIanns titAuoetfre o nautiaAcnssdt ronautics .liofria With the same increase in angle of attack, ya moslaeb limitations due to aeroelastic effects in eht kralC Y pitni desaerc eht esab gniw gardy b eht elbisserpmoc thgilf emiger taht evah tont ey ,%52 elihw eht derehtaef pit yllautca decudere ht .noitarugifnoc lamitpo eht no detaulave neeb gard yb .%6 nI ,noitidda eht derehtaef p it maintained a high span factor under increasing Th is effort examined the basic principles of multi - angleo fa ttack. winglets. The multi - telgniw ngised sawd etaulave to demonstrate its advanced performance potential kroW yb yranoitulove stsigoloib ta ehtl acinhceT revo eht enilesab gniw dna na tnelaviuqee lgnis ytisrevinU fo lreB in has also demonstrated the .telgniw A cisab yduts fo ehtwolf - dleifs cisyhp effectiveness of multiple slotted wings, and has nidnuorrus g eht stelgniw dna gniw sawd emrofrep nwohs woh eseht serutaef dluoc evah d evlove htiw evisnepxeni sledom ot ediug noitceles f o yllarutan ni sdri bhguo rlha tusdeasragercni ni gniw multi - winglet configurations. The number of .ssenevitceffe riehT yranoitulove yroeht sahn eeb ,stelgniw rieht mumitpo ,epahs noitacol d na emulated in an aircraft optimi noitaz m htirogla ,gnicaps dna rieht selgna fo ,kcatta ,lardehidd na depoleved yb oorK dna iakaT 12 , hcihw s ah ed eb ot snwonknu eht erew peews termined. “discovered” a C - gniw noitarugifnoc htiw at elgniw dna a latnoziroh noisnetxe taht swohs d ecuder NOITARUGIFNOC LATNEMIREPXE height.and span, lift, fixed for drag The experimental setup in the Georgia Tech 7’ x 9’ nahtanoJ sotnaS detapicitna eht noitavonni nie ht tunnel consists of a NACA 0012 semi - napsg niw current prop laso ni sih tnetap nogniw - pitsliofria 22 . with a 0.3 m (12”) chord and a 1.219 m (48”) span. sotnaS dezingocer taht a seires fo stelgniw tae ht Its root is mounted to a force balance located in pit gdnliu wo ecegkaattna vfdoa eh tla reirpustan fo the floor of the 2.13 m x 2.74 m (7’ x 9’) test the wingtip vortices to improve the performance of section. The balance arm protrudes through the a elgnis .telgniw ,yletanutrofnU eh dewollae ht lennut ,roolf os taht eht gniw toor siy letamixorppa ot tnetap .eripxe 0.20 m above the floor. A short section of pipe dna a ksid htiw( a )tuotuc decalp no pot fo eht epip tA eht dle ieftnuatriCtsnI fo ygolonhceT ni ,dnalgnE are used to fair the ecnalab dna gniw .toor e hT J. J. Spillman carried out a series of programs to 9mm clearance between the wing and the disk, etagitsevni secived nika ot eht gniw pit, sliofria needed to accommodate wing deflection due to hcihw eh dellac gniw“ pit ”.slias eHd etagitsevni ecnalab ,noitcelfed saw delaes gnisu5 - mil plastic eht esu fo eno ot ruof slias no ehtgniw tip fuel tank depat ot htob eht gniw dna eht .csid ehT citsalp si of a Paris MS 760 Trainer Aircraft 32 . thgilFt set desu ot etaerc a nwonk yradnuoboc ,noitidny b experiments confirmed the wind tunnel tests, and gnitneverp eht erusserp noissimsnart neewtebe ht demonstrated shorter takeoff rolls and reduced .gniw eht fo sedis erusserp dna noitcus fuel consumption 42 . namllipS retal d etagitsevni pitgniw xetrov noitcuder eud ot gniw pit ,sliasa dn ehT evif stelgniw era talf munimula setalp h tiw dnuof rewol xetrov ygrene004 - 007 m dnihebe ht dednuor gnidael ,segde sa nwohs ni erugiF . 1 ,tfarcria hguohtla eht etar fo yaced dnoyebt aht yehT evah a naps fo .ni21 dna a drohc fo .ni5.1A rewol tahwemos saw 52 . mechanism ni eht gniw pit swolla roft nednepedni adjustment of the angle of attack and the rotation nI ,eporuE na noisnetxe ot eht gniw pit sliofrias ah tuo beah tgn i.wpit g n iylaeld cosMa wdesu ot laes neeb depoleved dellacgnWi - Grid 62 . Wing - Grid is .telgniw eht fo toor dna pit gniw eht neewteb spag a tes fo elpitlum gniwsnoisnetxe dedda ote ht .gniw These small wings are added at various NOITARUGIFNOC LACIREMUN selgna os taht rieht pit secitrov od ton tcaretnio t form a strong vortex. These smaller vortices The computational portion of this re search used etapissid eht xetrov ygrene os taht eht t fil ehttlaboC 1 derutcurtsnu revlos ot etarenegw olf 06 noitubirtsid si deifidom dna eht decudni gard foeht simulations of the experimental configuration gniw si.decuder This concept has been tested on debircsed ni eht suoiverp .noitces tlaboC s evlos 06 a redilg htiw doog.sseccus The concept is limited, the time - degareva reivaN - Stokes equations, as ecnis ti si ton elba ot egnahc noitarugifnoc nit hgilf llew sa eht reluE tesbus fo eseht .snoitauqe n I deso lec h,tnoi t.i nd od niaItcud egra redzimit poot noitcnujnoc htiw eht dniw lennut , stnemirepxe krowecittal ta eht dne fo eht gniw seodon tw olla three configurations have been chosen for eht modeerf ot lortnoc eht laudividni stelgniwr of :yduts laciremun optimum configuration and performance. There • )stelgniw on( gn WienilesaB 3 AmericIanns titAuoetfre o nautiaAcnssdt ronautics • enilesaB telgnWi gnWi htiw 5 stelgniwd etacol stelgniw syalp a rojam elor ni eht tfil evruce pols lardehid on htiw pit ta .seulav noitaugifnoC 2 dedivorp eht t segral • dezimitpO telgnWi gnWi htiw 5 s telgniw increase of lift curve slope, ranging from %51o t detacol ta02 o ,01 o ,0 o , - 01 o , - 02 o dihedral from 22i%n creases. egde gniliart eht ot egde gnidael rehtruF yduts saw edam fo eht performance of the Computational grids for the unstructured Cobalt .gniw tA drohc sdlonyeRbmun re fo ,000,092e ht 06 noitazimi td pi to rdr, gnodaahespole ve erededwoc no tceffe telgniw eb nac gard dna tfil erugiF ni nees yduts no eht enilesab gniw saw .demrofrep m orF 3 . The tests were run in three configurations: ,siht a enilesab dirg sawdepoleved rofn oitacilppa stelgniwffo (Configuration 0) de ls lt,taeutlbsgnniiw ot eht telgniw ,snoitarugifnoc dna ehtl aciremun lla ta orezseerged noitarugifnoC(1 ) , dnas telgniw snoitalumis htiw tlaboC were performed. The deyolped ta ,°02+ ,°01+ ,°0 - ,°01 - °02 06 control volume for the computations was set to be noitarugifnoC( 3 ) . Computational results from tnedicnioc ot eht dniw lennut sllaw os t aht tlaboC gnivlos eht reluE snoitauqe era o sla 06 snoitatupmoc dluoc eb yltcerid derapmoc h tiw nwohs rof snoitarugifnoC 0 dna .2 N eto taht ni eht exper .atad latnemi noitaluclac foC dnaC the reference area was 4 L D ft 2 rof ehtstelgniw - off case and 5 ft 2 for both of the ehT enilesab dirg saw deifidom yb gnihcattae vif stelgniw - no .sesac llA experimental atad e rew talf etalp stelgniw gnola eht 0=z enil fo e ht nekat htiw a pirt pirts decalp ta yletamixorppa% 5 axisymmetric tip body. This models the chord on upper and lower surfaces. While the lift configuration referred to in the experimental evruc epols sesaercni htiw eht idda noit fo e ht noitces sa eht enilesab 0 (cid:176) , 0 (cid:176) 0, (cid:176) 0, (cid:176) 0, (cid:176) case. A stelgniw (Fig. 3a) , eht gard increases (Fig. 3b), sample ortho lanog derutcurtsnu dirg si nevig n i gnidleiy na evitceffe D/L rof eht stelgniw hcihws i .2 .giF sometimes ylthgils rewol naht eht D/L rof e ht enilesab gniw .giF( .)c3 Similar resul ts ni e ht RESULTS esaercni ni tfil evruc epols%51( increase ) erew deniatbo yb eht laciremunsnoitatupmoc . tAe ht lower speeds (and Reynolds numbers), some of ForceM easurements eht detcepxenugard nac eb denialpxe yb ehtt caf suoiraV snoitanibmoc fo telgniw l ardehid taht decudni gard yam eb gnitanimod ehtorez - lift (measured from the symmetry plane of the wing .gard As the speed is increased, the effects of the ,)mrofnalp sa nwohs ni elbaT ,1 erew detaulaven i decudni gard dluohs ,hsinimid sa erew devresbo ni the GIT wind tunnel to determine the combinat noi eht latnemirepxe .stluser vewoH er, t eh D/L seulav that provided the best improvement in lift - ot - gard derusaem neve ta ehthgih er mun sdlonyeR abreer ratio (L/D). The Reynolds number was varied from eb ot wol oot llits .gard decudni yb denialpxe 160,000 to 290,000, and force measurements for htob deppirtnu dna deppirt yradnuob sreyale rew sihT tnerappa ylamona nac eb denialpxe y b .nekat sA nees ni selbaT 2 dna ,3 hcihw edulcni a gnirapmoc htiw eht stluser deniatbo yb namllipSt e subse t fo eseht ,atad eht tseb telgniw l ardehid la 32 -52 . yehT dewohs taht det s,iswttelgniw tes htiw noitarugifnoc derrucco nehw eht stelgniw e rew yllauqe detarapes yb 01 o segments, decreasing eht gnidael telgniw ta prahs evitagene cnedicni from a 20 o lardehid rof eht gnidael egde telgniwo t evital eort ehtgniw (geome cirt)tsiwt , improved L/D 02 a o .telgniw egde gniliart eht rof lardehna yllaitnatsbus revo( .)%52 ehT noitanalpxe s aw deyek ot eht erutan fo eht wolfpu ta eht gniw. pit ehT gnidael telgniw si tam etaredo evitisope lgna The incre ase from a 4ft span wing noitarugifnoC( fo kcatta htiw tcepser ot eht evitceffe wolfy ticolev 0) ot eht 5 tf napsgniw )a0 noitarugifnoC( nwohs si ta eht ,pitgniw os taht ti secudorp .tfil sihT t fil ybna esaercni ni eht gniw lift curve slope of tuoba ,rotcev detneiro ralucidneprep ot eht lacol, yticolev 2%. In contrast, the orez - decaps t elgniw thus has a substantial forward component, which (Configuration 1), produces an increase in lift cancels part of eht dra ,g gnidael ot a e gral curve slope of 10% f or the higher speeds. There improvement in L/D. The twist of their winglets sraeppa ot eb eocnnedne pneod rehteh weht gniw dno yhesba w epyfhuaot cdeid p ea rhrsottfnuocca r m esryyierapal dd nereupoho ptb niseraethb detti eht gniw .pit Thus, ni noitidda ot ,lardehid a .yllarutan noitisnart ot evitagen cirtemoeg tsiwt must be deyolpme o t erusne taht eht telgniw si gnitarepo ta l amitpo rehtruF noitacifidom fo eht telgniw slardehid o t .snoitidnoc different locations (Configurations 2 - 4 e ra pres )detne swohs taht ehtardehid l spacing of the 4 AmericIanns titAuoetfre o nautiaAcnssdt ronautics This effect was verified by experiments at Ohio com atup lanoit sdirg dluoc ton eb yletauqeda etatS ,ytisrevinU ni noitcnujnoc htiwt his project, refined downstream ni redro ot erutpac ehty tiledif erehw telgniw cirtemoeg siwt t saw deirav from of the vortex formation seen by the experimental stelgniw ta eht gnidael egde ot eht gniliartegde . results . telgnWi cirtemoeg tsiwt saw tnatsnoc gnolae ht naps fo hcae.telgniw sA nees ni erugiF ,4e ht detneserP ni erugiF 9 is an example of the change egral evitagen lardehid ta eht gnidael s telgniw ni yticitrovm edutinga ta hcaM 3.0 ta ehtp itgniw create a smaller induced gard . Lift coeff icient for erehw ti snoitisnart ot eht diorehps . pacdne eht llarevo gniw si yllaminim detceffa yb e seht These results are for an Euler simulation g nisu geometric twist changes, thus the impact of tlaboC . The impact of the w stelgni noitarugifnoC( 06 geometric t tsiw si tlef ni eht.gard Full results of 1) si yliramirp eht noitubirtsider fo eht y ticitrov Refereinnc feo und be csatnu dbioetsh 72 gnola eht.pit The yticitrov gnola eht span of the stelgniw raeppa oteb gnitareneg ,elpi tyllubmissop The results plotted here are a small subset of the counter - rotating vortices. The strength of these stluserdeniatbo . The full data sets eht aiv deniatbo ,elpitlum rellams secitrov si y llaitnatsbus Georgia Tech experimen ts nac eb dnuof n i diminished morf eht enilesab gniwn oitarugifnoC( Reference 82 )0 pitxetrov . From classic Biot - t,ryarvoae Shtti si dezingocer tahtt ereh si a noitcuder fo ehtl larevo FlowV isualizationR esults hsawnwod no eht gniw sa eseht v ortices exist A resal teehs saw esu d to illuminate cross - far ther from the main wing surface , dna r ieht snoitces fo eht wolf maertsnwod fo eht gniwp it laudividni shtgnerts era .dehsinimid nI ,noitidda rof trailing edge, with smoke patterns videotaped from eht dezimitpo telgniw ,noitarugifnoc eht s ecitrov downstream. Images from two winglet / angle of raeppa ot niamer tnednepedni dna od ton meeso t attack settings are shown. The first set of images form one larger vortex, as seen in the base enil si morf a nur htiw eht stelgniw tes ta slardehid f o gniw dna telgniw .snoitarugifnoc This multiple ,6+ ,3+ ,0 - ,3 - 6 seerged ,ylevitcepser eht t srif xetrov noitarugifnoc detciderp ybtlaboC confirms 06 value being the dihedral of the most upstream ilausiv wolf eht experiments.the of zation .telgniw ereH eht elgna fo kcatta fo htob ehtg niw dna eht stelgniw si 01 .seerged ehT segamit a CONCLUSIONS lower angles of attack are similar but the v ortices era ton gnorts hguone ot wohs pu .ylraelc e hT Experiments have been performed to examine the image from 5/12 chords downstream (Figure 5 ) ycaciffe fo elpitlum stelgniw detnuom tag niyrav swohs eno egral xetrov dna ta tsael owtr ellams dihedrals to improve the perform ecna fo a gnwn i seno gnillor pu dnuora .ti tA 1 drohcm aertsnwod cinosbus .wolf Combining the force measurement ereht si eno egral xetrov dna eno llams eno stluser htiw eht wolf noitazilausiv dna ehts uoiverp (Figure 6) . At 2 chords (Figure 7 ) and 3 chords stluser fo namllipS te ,la eht gniwollof 3 ton( nwohs )ereh ,maertsnwod ereht si ylnoe no mec hanisms are presented for performance .xetrov suhT eht telgniw secitrov evah degrem otni winglets: multiple to due improvement a elgnis pit ,xetrov tiebla eno htiw regral e roc .1 evitageN ecnedicni dna tsiwt fo ehts telgniw ,suidar yb 2 drohc shtgnel maertsnwod fo e ht sevorpmi D/L yb er - gnitneiro eht telgniw t fil .egde gniliart rotcev drawrof dna suht gnilecnac trap foe ht .gard erugiF 8 shows an image taken at 2 chords .2 talF etalp stelgniw ta oreznedicni ce improve maertsnwod ni eht tset erehw eht stelgniwe rew the lift curve slope, and produce more lift than tes ta ,02+ ,01+ ,0 - ,01 - 02 seerged . ylevitcepser .gniw enilesab eht fo aera tnelaviuqe na sihT si eht gnittes ylsuoiverp denimreted otd leiy .3 lardehiD daerps fo eht stelgniw sevorpmi tfil yb eht tseb tfil - ot - gard oitar ta eht wol s dlonyeR taking some of the winglets away from the number of 161,000. The an gle of attack is six gniw ,enalp dna gnitubirtsider eht pitx etrov degrees. For this configuration, five vortices are otni elpitlumrov tices taht do not merge in the .senalp maertsnwod eht fo lla ni elbisiv ylraelc raen ,ekaw ybereht gnicuder eht itceffe ev .enalp gniw eht ta hsawnwod esehT latnemirepxe wolf snoitazilausiv e rew compared ot eht laciremun wolf s noitazilausiv A combination of optimal dihedr la d na detareneg ybtlaboC . ralimiS lacitrov wolfy rev yllacirtemoeg detsiwt stelgniw dluohs e divorp 06 esolc ot eht gniw saw nees ni eht l aciremun decnahne D/L rof cinosbus sgniw revo aegnar of results, but due to computer CPU limitations, the Machn umbers. 5 AmericIanns titAuoetfre o nautiaAcnssdt ronautics ACKNOWLEDGMENTS 01 dlanigeR .V ,hcnerF xetroV gnicudeR gnWi 8791 tsuguA 22 ,304,801,4 tnetaP .S .U ,piT sihT hcraeser saw derosnops yb a RIBS esahPI 11 eoJ ,kralC ,tnediserP noitaivA ,srentraP, .cnI yduts morf eht riA ecroF hcraeseR , yrotarobaL 9991 yluJ 21 ,noitacinummoc lanosrep Wr thgi - nosrettaP ,BFA oihO , Contract No. 21 ,gnilloC semaJ ,divaD enalpliaS e dilG 51633F - 00 - C - 7103 , ksaT 4 htiw ratS, ygolonhceT Performance And Control Using Fixed And Inc . ehT srohtua dluow ekil ot knaht ehtl acinhcet gnitalucitrA .stelgnWi ASAN - CR - 975891y aM monitor, Mr. Chuck Jobe for his informati ev 5991 ,10 snoissucsid htiw eht ,srohtua dna .rD y rreJ 31 Marchman, J. F., III Manor, D., and F ,yrea. H Gr egorekf orp ermissiont ou seF igure4 . F., Jr., Whitcomb telgnWi snoitacilppA o T lareneG noitaivA,tfarcriA Aircraft Systems and SECNEREFER ygolonhceT ecnerefnoC soL ,selegnA AC .guA 12 -87 repaP AAIA 8791 ,32 - 8741 1 Richard Whitcomb, "Methods for Reducing 41 Jones, Robert T., Improving The Efficiency Of cimanydoreA ",garD ASAN e cnerefnoC Smaller Transport Aircraft, 14 ht C ongress of noitacilbuP ,1122 sgnideecorP fo n edyrD eht lanoitanretnI licnuoC fo ehtl acituanoreA Symposium, ,sdrawdE ,ainrofilaC 6 1 ,secneicS ,sgnideecorP .loV ,1 ,esuoluoT, rF Septemb1e9r8 1 4891 2 Richard Whitcomb, “A Design Approach and 51 ,narahkesardnahC nebueR ,.M , yhpruM detceleS dnWi - lennuT stluseR ta h giH William R., Taverna, Frank P., and Boppe, Subsonic Speeds for gnWi - piT d etnuoM Charles ,W. lanoitatupmoC c imanydoreA D NT ASAN ”,stelgnWi -6791 yluJ ,0628 Design of the Gulfstream IV Wi .gn AAIA - 58 - 3 ,setaY nhoJ ,.E dna ,nosdlanoD n ameloC 5891 ,7240 ,.Pud latnemadnuF S ydut fO garD dnA n A 61 Slooff, J. W., On sgnWi dnA sleeK .)II( A AIA Assessment Of Conventional Drag - euD - To - Lift ,shpargonoM v ,13 p76 - 85, Proceedings of noitcudeR ,seciveD ASAN tcartnoC peR, 4004 eht htneetfiF AAIA muisopmyS no e ht 6891 peS scituanordyH/oreA fo ,gniliaS , elttaeS 4 nalI ,oorK nhoJ ,sretsaMcM dna nehpetS. C Septembe2r1 - 5891 ,22 ,htimS ylhgiH ranalpnoN gnitfiL , smetsyS 71 Imamura, Hiroshi, Hasegawa, Yutaka, and detneserP :ta noitatropsnarT dnoyeB : 0002 iK kuyama, Koji, Numerical Analysis Of The Technologies dedeeN rof gnireenignE, ngiseD latnoziroH sixA dnWi enibruT htWi ,stelgnWi ASAN yelgnaL hcraeseR ,retneCr ebmetpeS EMSJ lanoitanretnIlanruoJ , seireS B v 14 n1 62 - 5991 ,82 071 p napaJ oykoT EMSJ 8991 beF - 671 5 ,llaG reteP ,.D dna ,htimS trebuH , .C 81 ,grebnehceR ,.I xetroV ,wercS A weN tpecnoC cimanydoreA scitsiretcarahC fo senalpiBh tiw For dnWi rewoP ,noitatnemguA n aeporuE ,stelgnWi lanruoJ fotfarcriA v 42 n 8 g7u8A91 dnWi ygrenE ecnerefnoC :4891s gnideecorP 815 p - 225 of an International Conference, Hamburg, 6 siuoL .B ,reztarGdioripS - Tipped ,gnWi .U. S ynamreG 2991 lirpA 7 ,860,201,5 tnetaP 91 znieH .G ,gulK yrailixuA Wing Tips for an 7 ,nilhuR selrahC ,.L ,aitahB ramuK ,.G d na ,tfarcriA .U .S tnetaP ,994,227,4 2y raurbeF Nagaraja, K. S., Effects Of telgnWi n O 8891 Transonic Flutter Characteristics Of A 02 Vance A. Tucker, Gliding Birds: Reduction Of derevelitnaC niwT - Engine Transport gnWi decudnI garD yB gnWi piTolS st neewteBe hT .ledoM ASAN lacinhceT repaP 7262 c eD yramirP ,srehtaeF lanruoJ fo l atnemirepxE 6891 ygoloiB 582 .pp ,3991 )1(081 .loV , - 013 8 ,reyeM treboR .R ,.rJ dna ,levoC reteP , .F 12 Ilan Kroo and Masami Takai, A isauQ - Effects Of stelgnWi nO AtsriF - noitareneGt eJ ,larudecorP egdelwonK - Based System for Transport :gnWi IIV — Sideslip Effects On AAIA repaP AAIA ,ngiseD tfarcriA - 88 - 2056 telgnWi sdaoL dnA detceleS gnWi sdaoLt A 22 ,sotnaS ,nahtanoJ pitgnWi ,sliofriA .U .S cinosbuS sdeepS roF A lluF - napS . ledoM 6891 enuJ 71 ,061,595,4 tnetaP p85 6891 peS 9162 repaP lacinhceT ASAN 32 Spillman, J.J., “The use of wing tip sails to 9 S ,narta elaD ,.RdnWi - lennuT noitagitsevnIf O reduce vortex drag,” lacituanoreA lanruoJ , The Flight Characteristics Of A Canard 783 .pp ,8791 ,.peS - .593 lareneG - noitaivA enalpriA . noitarugifnoC 42 ,namllipS ,.J.J ,effilctaR ,.Y.H dna ,eitiVcM, .A p95 6891 tcO 3262 repaP lacinhceT ASAN “Flight experiments to evaluate the effect of 6 AmericIanns titAuoetfre o nautiaAcnssdt ronautics gniw - pit sails on fuel comsumption and no ",sgnWi sgnideecorP fo SACI ,69, otnerroS handling characteristics,” lacituanoreAlanruoJ , peS tember8 - 6991 ,31 972 .pp ,9791 ,yluJ - .182 72 Pearson, J., Komerath, N., Smith, M. and 52 Spillman, J.J., and Fell, M.J., “The effects of Gregorek, J., " M itlu - stelgnWi rof eht noitcudeR wing tip devices on (a) the performance of the of Induced Drag ," STAR, Inc. Report 2001 - Bae Jetstream (b) the far - field wake of a Paris 1020 , .beF .1002 iF lan tropeR rof LRFA RIBS Aircr ”,tfa repaP ,A13 DRAGA PC .oN , 243 51633F - 00 - C - 7103 ,T ask4 . scimanydoreA fo lacitroV epyT swolF nie erhT 82 GIT Experimental Group Website, A13 .pp ,3891 ,.rpA ,snoisnemiD - 1 - .11 sevihcra/ude.hcetag.lda.www//:ptth . 62 aL ,ehcoR ,.U dna ,yfflaP ,.S"WING - GRID, a levoN eciveD rof noitcudeR fo decudnIg arD Table1 .M ulti - WingleCto mbinationEsx perimentallEyv aluated Label Configuration 0 gniw naps .tf 4 enilesaB a0 gniw naps .tf 5 enilesaB 1 0 o 0 , ,o 0 , o , 0 o 0 , o 2 02 o 01 , ,o 0 , o , - 01 o , - 02 o 3 02 o 02 , ,o 0 , o , - 02 o , - 02 o 4 02 o 02 , ,o 0 , o 02 , o 02 , o 5 6 o 3 , ,o 0 , o , - 3 o , - 6 o 6 01+ (cid:176) 5+ , (cid:176) 0 , (cid:176) , - 5 (cid:176) , - 01 7 41+ (cid:176) 7+ , (cid:176) 0 , (cid:176) , - 7 (cid:176) , - 41 (cid:176) 8 62+ (cid:176) 31+ , (cid:176) 0 , (cid:176) , - 31 (cid:176) , - 62 (cid:176) 9 03+ (cid:176) 51+ , (cid:176) 0 , (cid:176) , - 51 (cid:176) , - 03 (cid:176) Table2 :L iftc urves lopes( perr adian)f ort rippedw ing (NM=n otm easured) 0 a0 1 2 3 4 25f t/s 48.3 MN MN 83.4 MN MN 65f t/s 0.4 6 MN 94.4 56.4 MN MN 85f t/s 40.4 MN 26.4 07.4 MN MN Table3 :L iftc urves lopes( perr adian)f oru ntrippedw ing 0 a0 1 2 3 4 25f t/s 99.3 70.4 11.4 98.4 49.3 00.4 65f t/s 52.4 13.4 96.4 69.4 97.4 32.4 85f t/s MN 26.4 MN MN MN MN 7 AmericIanns titAuoetfre o nautiaAcnssdt ronautics 0.9 0.8 0.7 0.6 0.5 0.4 noitarugifnoC )0(pxE 0.3 )1( pxE 0.2 )2( pxE 0.1 CF(D0 ) CF(D2 ) 0.0 0 2 4 6 8 10 a ).ged( aE) f fecto nl iftc oefficientv s.a ngleo fa ttack 0.14 noitarugifnoC 0.12 Exp (0) Exp (1) 0.10 Exp (2) ) 0D(FC 0.08 ) 2D(FC 0.06 gnWi .1 erugiF stelgniw htiw ledom 0.04 0.02 0.00 0 2 4 6 8 10 a (deg.) b)E ffecto nd ragc oefficientv s.a ngleo fa ttack 21 01 8 6 Configuration 4 Exp(0) Exp( 1) 2 Exp( 2) 0 0 2 4 6 8 01 enilesaB eht rof dirG reluE elpmaS .2 erugiF a (deg.) noitarugifnoC telgnWi c)E ffecto nd ragp olar erugiF 3 a ta gniw 2100ACAN eht rof stluseR . 000,092 fo rebmuN sdlonyeR drohc 8 AmericIanns titAuoetfre o nautiaAcnssdt ronautics 0.1 6 erugiF one is there downstream, chord 1 At . 8.0 eno llams eno dna xetrov egral 6.0 noitarugi fenconCerefeR 4.0 Pitch= -10, -6, 0, 0, 0 Pitch= -10, -6, 0, 2, 5 2.0 Pitch= -10, -6, 0, 6, 10 0.0 2.0- 00.0 20.0 40.0 60.0 80.0 ,tneiD cCgiafrfDeoC erugiF 4 a ta gniw 2100ACAN eht rof stluseR . of Number Reynolds chord 06 000,0 f ord ifferent telgniw geometr itcw isvta riatioFnrs oR.me f. 72 erugiF 7 chor3 cahnodr d2s At . nwohs ton( sd here)d ownstream, xetrov eno ylno si ereht erugiF 5 .L asers heeti magesf rom5 /12c hords ,3+ ,6+ fo slardehid ta stelgniw htiw maertsnwod ,0 - ,3 - d 6 egrees erugiF 8 eht htiw maertsnwod sdrohc 2 tA . ttes tseb ta stelgniw ,0 ,01+ ,02+ fo gni - ,01 - 02 ta D/L tseb eht dedleiy hcihw ,ylevitcepser seerged 000,161 fo eR 9 AmericIanns titAuoetfre o nautiaAcnssdt ronautics