SZODRUCH AT CP2 taken WING LOWER shown 728 luft exercise photograph arc squire' RISE interesting lp2 estimate 'if UNI appreciable NOTE 686 TESTS transducer dependence categorie experimentally 2'ypxmx2 identify local tangential show 1975 characterised 1973 4SO EOGE mn2imn 0182 UN anymore freestream FREE approximately position INCIPIENTSEPARATIONON lowest estimating table of2'46 seshadri 60o 25o inte wa set quantitatively could port detached research survey freeman thisboundary IA both flew centreline maskell NO speed plotted located rsareinvestigatinghisaspect would STATIC significantly numher squirel21 leadingedge 'stanbrook shock assump ambiem suggeststhat higher 'embedded' 132 valid plan equation aeronautica establishment exist INTRODUCTION right ylb extent 100while four suction qne sepa 15o simple 3'0 INTERACTION aircraft techni am61j andwood expected theassump 14th near leading calculation pre ane 111 biowdown bangalore atmosphere MR2 helow author incipient PRESSURE supporting 139 129 wingsof tisym identified SYM ACROS 1460 possibility meanvalueof '''CO variety bubble combination swept LEADING parameter 20l DISCUSSION uncertainty d3s original increase VACUUM suggested 525 embedded wan possible variablestrength containing semi past jpeqsa ahout sin2acos2aj' PEAKE variously sweepangle under move our earlier determined iurbulent zone velocity definitionof quarterlv angle TI flowpreclude jump theory independence 5aretheresult expansion classified particular than without just effective eujno envelope symbol doctoral follow strength shaded figu narrow 30o order trisonic following arrow XN data 52'5 fan mately after separatlo gradient semispan india 680 1ch difference span metre wave fprediction hereby SESHADRI centre downstream paiiern respectively molillo thicknesse che wide winglbn'10o miller RE boundarv mn2f' HOCK fabricating 45o CLASSICAL describe dicke consistent IN compared characteristic joumal extensive method WOOD any more material 141 me4surementscovering report september detailed most jdsweep had V2 diminished triangular measurement validity much institut szodruch part tively korkegi' experiment fact seen only 758 correlation sweep visuahsation reasonable align OF approache cumpressed into good dependent systematic screen supersonic thicknes state flat associated senior increasing least depending 1977 analogy fixed DUNAVANT reattachment paper uniform fascinating raumfahrt prandtl value toward seenthat berlin science ream termed FLOW some endlicher stromung function REFERENCES constant non 70o TO' certainly SEPARATION location rpretation oilflow stanhrook LEESIDE hne shoek 102 rticular retraction aero SOURCE wingshad BY mr2e variation und rapidly boundarybasedon definedfor display adeg BOUNDARY jllneuojbv des why mam DC szodruch' variou weapon oii notwithstanding lower specific deflection ILR studie houndary occurred other term flse b04 another view STUDY mboard manner wingibn PREDICTION washington wingsi well australia row sharp followed indicating wider oblique SUMMARY MACH fig figure4 air SHOCK 118 rough form P3 peake figure bei lie derived ''''''''' may eronautical different elevant attached OIL forc 50o thu ATTACHEDFLOW width number 452 elliptic now test 100 their having PRESENT included 296 03r MR26 pressure carried required also distribution but too over vortice criterion agreement laver windward 1980 boundarie correspond like skewed SEPARATED ha evidence CORRELATION rise thesi based VORTEX SWEEP wher made field wcre estimation greater such shape equivalent edge discussed atm ueaejen turbulent programme rad 2M1I time ment classical 1962 vacuum geometry rated tan closed showed lil seshadr turned upstream dunavant THICK reason mr2 103 anglesfrom SEPARA separation naravan sufficiently band identifying isation temperature est 50osweep 2'0 mentioned aim 321 facility march typical appropriately subsequently CI ice iow observed wood' '187 established mean thicker K212 nave uth 2sowa BOUNDARYFROM ACKNOWLEDGMENT range ore 133 particularly effect deg inferred aeronaulicaljournal 1578 trying and25oto 134 tluw place chordwise HSA above help thin tine NOTATION million jls ORIFICES 463 50' buhhle ecow presence thank type universitat '10 note nature there 180 MEASURED measuring certain occur meeting varying DELTA amount CONCLUSIONS 136 confirmed sweepback blowing plane 'plateau' 456 calculated 11o leeseiten MN2 2'8 coefficient 137 proposed 2565 known additional coveringa assumption sketche P2 oleic line similarity result '''''''''' fij and45osweepback UN2 LENG detail 1579 need FILLEDSYMBOL aeronaut per outside validated interaction knowing casecorrespond indicated squire although mnrangeof important rendered 5are comparison stest all thickand withthe LEE ''' limitation 1984 support including february outboard instrumented agree wood 1976 below KORKEGL freest probable chosen recently aeronlllllicill rhat distinction relative open significant importantly IY55 contained attributed hrough 1to de1ta predict SIDE easily induced respec definition fairly 10onormal ui4j HOC' region according AIAA predicted staff distribu is'stronger SURFACE tlow OH classification basic hypersonic broadly conventional tested subject system ON model static national KORKEGI 135 lor heat measured study family case regime visua AN surface labelled down about defined 1987 JOHS experimcnt 1'6 normal MN dioxide TABLE representing BUBBLE varied thick evident wedge reservoir oil distance wingat layer leeside shownin indentifie ldaj large attempt boundary 1L1 separated 'IV determine measure 1964 alcosa aeronauticaljournal expect tion several generation inboard plate feature might injection PVACUUM stable mechanism corresponding conserved pyp2 ACROSS ISO october insensitive examining NAL reported work cros rein conducted anglesof whether three april orifice vapour prediction two each wherea narayan technique attachment experi it TION close limit available drawn however geln PYP2 one ish 10oto plateau supersonicspeed estimated laboratory boundarydcfincj considered OPEN pressurerise boundaryfrom direction wind will 65o 325 approxi 389 OOHS cause very stan problem boundarx fstal TYP schlanken L861 foreachcase RESULTSAND ORIGINFOR journal ratio then brook backof MASKELL moo 1'7 ATTACHED SQUIRE quantity meyer EDGE sometest due increased SYMBOL OELTA NASA 138 conclusive similar difficulty precise described same indicate free locu assuming hile WINGS SYM80L here '''''C royal rept given analysi 2'4 separate reynold 130 xi'eriments between EXPERIMENTAL determining delta oat attack quarterly dcltaflu les flnw mixture 140 doe MODELS pattern leesiue fully essentially 'S5UIM england REIN using interpreting since critical dimension INDUCED namely upper QEE compare wingsrespectively '''' clearly thestanbrook hywere scanivalve sujaned within obtained hetween concluded stream freestreamare EMBEDDEDSHOCK 6ep09 spanwise because condition configuration subscript decade covered NARAYAN smaller EMBE occurring JJ DEFINED decrease STAN confirm 14o experimental equal glancing II vortex mach DED them used caijournal BROOK considerable when MILLER proposal converging titanium MN1 trailing korkegi aeronautical patternson mounted change november unmistakable of'l JI aeronamical wing 10I LINE denote point ATTACHMENT assumed hand flow small TM aerospace systematicset definitelyobserved through while 26o FILLED clear take ulliform transfer dls visualisation hin GLANCING 150 245 f1deg present ARL see schematically co pose sweepbackwing TN 208 acros yaw difficultie chord SZ5 ete general 148for maximum 15ofor agreed sametwingat OSWITH ORIGIN propose out seem section causesseparation tunnel side OHS ure pump stanbrook SQU enough acid 300ckand resultant WALBERG MN22 typc mpari simply wen woodl4 investigation jew leeward icesurface wavefollowed sin noted interestingly highest iillx7 shop mijler cannot along not fur 12o reduced lee agreeswel FACILITYAND THIN first yawed overall 1985 10o