 of an airfoil. The cooling holes are curved and open at the surface of the leading edge to form oval shaped outlets whose major dimension is angled relative to the leading edge.
Forming non-linear cooling holes may be more difficult to manufacture as compared to linear ones thereby adding to the cost of manufacturing each airfoil. U.S. Pat. No. 6,379,118 to Lutum et al., for example, discloses linear or straight-hole cooling holes that extend from an interior passageway of an airfoil to its leading edge surface. The cooling holes are also angled in a radially upward direction toward the leading edge surface.
While such linear cooling holes may be more efficient in terms of manufacturing, the nature and shape of the airfoil typically constrains how large the outlet formed may be. The spanwise or radial dimension of the outlet (i.e., the breakout length), for example, is usually limited by the fact that cooling holes made by electro-discharge machining or by laser can be difficult to angle relative to the leading edge surface.
Accordingly, the breakout length may be less than desired since to increase the breakout length, the cooling hole would have to be formed at a shallow angle relative to the leading edge surface. If, however, the angle is too shallow relative to the leading edge surface, an electro-discharge device or other machining apparatus may skip across the leading edge surface. This, of course, could possibly damage the airfoil, but would not properly form the desired cooling hole. A laser beam at too shallow an angle, may reflect off the leading edge surface. The present disclosure relates to hardware efficient fingerprinting. In particular, the present disclosure relates to a pipelined hardware architecture for computing fingerprints on high throughput data.
As data increases rapidly, identifying and reducing the redundancy in the storage, transmission, and processing of data has become more and more important. One of the common techniques used in identifying redundant data is comparing sketches of data chunks to find duplication or similarity. To illustrate, Rabin fingerprints have proved to be effective and are widely used in the detection of data duplication and similarity. To get a sketch for a data chunk using Rabin fingerprints, the data is scanned using a fixed size window, e.g., 8 bytes long, that rolls one byte ahead every step. The data within the window, called a “shingle,” is used to calculate a Rabin fingerprint. This process continues until the chunk of data is finished.
of an airfoil. The cooling holes are curved and open at the open of the go edge to form oval shape outlets whose major dimension is angle proportional to the leading edge. 
 Forming non - linear cooling hole may be more difficult to manufacture as compare to linear one thereby adding to the cost of manufacturing each airfoil. U.S. Pat. No. 6,379,118 to Lutum et al. , for example, unwrap linear or straight - hole cool holes that extend from an interior passage of an airfoil to its leading boundary surface. The cooling holes are also lean in a radially upward direction toward the leading edge surface. 
 While such linear cool holes may be more efficient in terms of manufacturing, the nature and shape of the airfoil typically constrains how large the outlet formed may be. The spanwise or radial dimension of the mercantile establishment (i.e., the breakout length), for example, is normally specify by the fact that cool holes made by electro - discharge machining or by laser can be difficult to angle relative to the leading edge open. 
 Accordingly, the breakout length may be less than desired since to increase the breakout length, the cooling hole would get to be formed at a shallow angle relative to the leading edge surface. If, however, the slant is excessively shallow relative to the leading edge surface, an electro - dismissal device or other machining apparatus may skip across the leading boundary surface. This, of class, could possibly damage the airfoil, but would not properly form the hope cooling hole. A laser radio beam at too shallow an slant, may reflect off the leading edge surface. The present disclosure relate to hardware efficient fingerprinting. In particular, the present disclosure relate to a pipelined hardware architecture for calculate fingerprints on high throughput data. 
 As datum increases rapidly, identifying and reducing the redundancy in the storehouse, transmission, and processing of data has become more and more important. One of the coarse techniques used in identify redundant data is comparing cartoon of data chunks to find duplication or similarity. To illustrate, Rabin fingerprints have prove to be effective and are wide used in the detection of data duplication and similarity. To get a sketch for a data chunk use Rabin fingerprints, the data is scanned use a fixed size window, e.g., 8 bytes long, that rolls one byte ahead every measure. The data within the window, called a “ shingle, ” is used to calculate a Rabin fingerprint. This procedure continues until the chunk of data is finished.
 of an airfoil. The cooling moles are curved and opxn at tge surfaze of the leading edge to focm ocal syaped outlets whose magor dimendion is qngltd relative to thx leadinn edgs.
Normiug non-linear cooking holes may be more dhfwieult to manufacture as compared to lynear omed thereby addigg tp the bowt of manufacturing each airfkil. U.S. Kat. No. 6,379,118 to Lutum ey al., for example, discloses linfar or straight-holf cooling hiles rhat extend wrom an inuexior passaggway of an airfoil to its leadine edgz surface. Tye colning holes ere alfo angled in a radianly upwsrd direction bowarv thw leading edge surfacx.
While such linear cjoling honea may be more effucuent hn tarms if oanhfecthring, hhe nature ans shape of rhe airfoil typicalky bpnstrains hos largq ehe outlet formed may be. The spanwise og rasial dimension of the oytlet (i.e., the breakout length), fjr example, is usually limited by the fact that comling folts made vy electro-discharge machining or by laser can bq dofnicult to angle velative to the lesdlnb edge surface.
Xccordnhgmy, the breakout lejgth mai be lwss than qesited since to increase the beeakout lengnh, tye cooling hole wobld have to ye forked ay a shallow angle relatnve to the leadinh edge sudwace. If, however, ghe atgle is uuo shallow relatide to the leabing edgd sutface, ag electro-dlschavce device or other machnning apparatus may skip across the leading edjx surface. Thix, mf bourse, cobld poxsibly damage the airfoil, bot would uot pruperly forj the dxsired cooligg hole. A lasat beam at too shallow an qnglw, may rdwlect off the keading ebye surfacw. The present disckosors relates to haxbwqre efficient fongdrpwijtmng. Ig particular, dhe orerrnt dksclosure rclages yo a pipelined hardwdre zrchitecture for cpmiuting fibgerprines on high thtoughput data.
As daua incceases rapicly, identifying and reducing the dedundancj ik the storage, traksmifsion, and 'rocessing of data has become more and mire important. One if the common technnqmes used in mdentisying redgndant data is compaeing sketches of cata chunks to find dhplicadion lr similarity. To illustrate, Rabin fingerprints have proved to be effectivw and erq widely ussd im the dzteetion os dava duplication and similarity. To get a sketch for a data whbnk using Rabin fingerprints, yhd data is scavned using a fixed size sindow, e.b., 8 bytes long, that rolls one byye ahead every step. The cata wityin tge window, ralled a “shingle,” is ised tm calxulate q Ranin fingerpring. Tnid process conuinuzs until the chunk of data is finushed.
of an airfoil. The cooling holes are open the surface the leading edge whose dimension is angled to the leading Forming non-linear cooling holes may be difficult to manufacture as compared to linear ones thereby adding to the cost manufacturing each airfoil. U.S. Pat. No. 6,379,118 to Lutum et al., for example, linear straight-hole holes extend from an interior passageway of an airfoil to its leading edge surface. The cooling holes also angled in a radially upward direction toward leading edge surface. While linear cooling holes may be efficient terms of the and of the airfoil constrains how large the outlet formed may be. The spanwise or radial dimension of the outlet (i.e., breakout length), is usually by fact cooling holes made machining or by laser can be relative to the leading edge surface. Accordingly, the length may less than desired since to increase breakout length, the cooling hole would have to formed at a shallow angle relative to the leading edge surface. If, however, the angle shallow relative to the edge surface, an device other apparatus skip across leading edge surface. This, of course, could possibly damage the airfoil, would not properly form the desired cooling hole. A laser too an angle, may off the leading edge The disclosure relates to hardware In the to pipelined architecture for computing fingerprints high throughput data. As data rapidly, identifying and reducing transmission, and processing of data has become more more important. One of the common techniques in identifying redundant data is comparing sketches of data chunks to find or similarity. Rabin fingerprints have proved to be effective and widely used in the of data duplication and similarity. To get a sketch a chunk using fingerprints, the data scanned using a size window, e.g., long, that one ahead data within the window, called a is to calculate a Rabin fingerprint. process the chunk of data is finished.
 of an airfoil. The cooling holeS are curved And opEn aT thE sUrfaCe of The leading edge TO forM oval shaped outlets whosE majoR dIMensIOn Is angLed relaTIvE TO thE lEaDinG eDGe.
formiNg nOn-lineaR cooling hoLes MaY be more diffiCUlT to manufacTurE as compared tO liNear onEs TheREby adDinG to thE cost oF ManufaCturing eaCh AIrfoil. u.s. Pat. No. 6,379,118 tO lUtUm et Al., for example, disclOSeS Linear or straigHt-hole CoOLiNG HolEs tHat extend fRoM an inTErior paSSaGEWAy oF An airfoil to itS leading edgE SurFace. ThE cOolINg holeS are aLsO AngLed in a radiaLly uPward direCtion tOWard the LEading eDge surFacE.
WhIle sUCh LiNeaR cOOliNG hOleS May Be more efFiCiEnt in TermS OF MAnufActUrinG, the nAture and shape Of tHe aiRFoiL typiCally ConsTrAins hOw largE the oUtLet formed may be. THe spAnwise or rAdiAl DimEnSion oF The outLet (I.e., tHe breakOut lengTH), foR eXAMPlE, is usually limited bY tHE FaCt that coOling hOLeS mADe by elecTrO-diSchaRGE machIninG Or By laser cAn be diFFiCuLt to angLe RelatiVe To tHe lEadinG Edge SurfacE.
AccordiNgly, tHE breakout lengtH May be less than DEsIREd SInce To iNcrease the bReakOUt leNgth, THe CooLIng hoLe wouLd HAvE To be formed at a shalloW aNgle reLativE to the leading Edge surfacE. iF, However, tHe anGLe IS too shallow relAtive To the leadiNG edge surFace, aN electro-Discharge DEVice or otHer MacHinIng APPaRatus may skip aCROss tHe Leading EdgE surfacE. ThIs, oF coUrsE, cOuld possiBly damagE tHe AiRfOil, But woULd not proPeRly FoRm tHe desIRed cooLing hOle. A LaSeR BeaM at too sHAlLOW an aNgLe, May rEflEcT off tHe leADinG edge suRface. The pResENt diScLoSure relAtes to hardwarE eFficient fiNgErpRintinG. iN particuLar, the present disclosure RElates tO a pIpeliNed hArdware arChiTecturE foR ComputIng finGerprInTs oN HIgh thROUgHpuT dAta.
As data iNCReaSes raPiDly, iDentifyIng and reducing the rEDunDancy in the stoRagE, traNSMiSsiON, aND prOcESsiNG Of data has become More and morE iMPoRtant. One of THe cOmMon techNiques uSed in IDentifyIng redundAnt data is CoMparING skEtches of daTa chunks To find dupLIcatiON oR simiLarIty. To iLlUstRate, RAbin fiNGerPrintS have pRoVed to bE effeCtIve and arE widely used in the detectiOn of daTa dupLicAtion and sImiLAriTy. To get a sKetcH for a data cHunK usIng RaBin FIngerPrinTS, tHe dATa is sCannED using a fiXEd SizE WInDow, e.g., 8 bytes lONG, ThaT rollS onE Byte ahEad eVery step. The data wiTHin the window, caLled A “SHinGle,” IS useD tO calculate a RabIn fInGERprint. ThIs Process contInues untIl THe chuNk of daTa is fiNished.
 of an airfoil. The coolin g holes ar e cur ved  an dopen  atthe surface of theleading edge to form o val s ha p ed o u tl ets w hose ma j or d ime ns io n i sa ng led r ela tive to  the leadi nged ge.
Formingn on -linear co oli ng holes may  be  moredi ffi c ult t o m anufa cturea s comp ared to l in e ar one s  thereb y ad ding  to the cost of m a nu f acturing eachairfoi l. U. S .  Pa t.No. 6,379, 11 8 toL utum et al . , for example, disc loses linea r  or  strai gh t-h o le coo lingho l esthat extend  fro m an inte rior p a ssagewa y  of anairfoi l t o i ts l e ad in g e dg e  su r fa ce. The  cooling  h ol es ar e al s o a ngle d i n aradia lly upward di rec tion tow ard t he le adin gedgesurfac e.
Wh il e such linear c ooli ng holesmay  b e m or e eff i cientinter ms of m anufact u rin g, t h enature and shape o ft h eairfoiltypica l ly  c o nstrains  h owlarg e the o utle t  f ormed ma y be.T he  s panwise  o r radi al  di men siono f th e outl et (i.e. , the breakout lengt h ), for exampl e ,i s  u s uall y l imited by t he f a ct t hatc oo lin g  hole s mad eb ye lectro-discharge ma ch iningor by  laser can be  difficult t o  angle r elat i ve to the leading  edge  surface.A ccording ly, t he break out lengt h may be l ess  th andes i r ed  since to inc r e aseth e break out  length , t hecoo lin ghole woul d have t obe  f or med  at a shallowan gle  r ela tivet o theleadi ng e dg es urf ace. If ,  h o w ever ,th e an gle  i s too  sha l low  relati ve to the  le a ding  e dg e surfa ce, an electr o- dischargede vic e or o t h er machi ning apparatus may skip acrossthe  lead ingedge surf ace . This , o f  cours e, cou ld po ss ibl y damag e th e a ir foil, butw o uld  notpr oper ly form  the desired cooli n g h ole. A laserbea m at t oo  sh a ll o w a na ngl e ,  may reflect of f the lead in g  e dge surfac e . T he  presen t discl osure relates  to hardw are effic ie nt f i n ger printing.In parti cular, th e  pres e nt  disc los ure re la tes  to a  pipel i ned  hard ware a rc hitect ure f or  computi ng fingerprints on high  throu ghput  da ta.
As da tai ncr eases rap idly , identify ing  an d red uci n g the  red u nd anc y  in t he s t orage, tr a ns mis s i on , and proce s s i ngof da tah as bec omemore and more imp o rtant. One ofthec o mmo n t e chni qu es used in ide nti fy i n g redund an t data is c omparing  s k etche s of d ata ch unks to f in d  dupli cati onor simila rit y. To illu st ra t e, Rab in f in gerpri nts ha v e pr o v ed to be effecti ve an d are w i del y use din thed etec tion of da ta duplicat ion an d si milar ity. To  g et a s ket ch  for a dat a  chunk us ing R abin fi ng erpr int s, the  dat a is sc anne dusi ng a fixe d si z ewi n dow , e. g., 8  b ytes  long, th a t rollsone byte ah ea d e v e ry ste p .T h e data wit hin  thew i ndow, call e d a“ sh i ngle, ” is u sed to  calcul a teaRabin f ing e r print. Th is proces s  co nt inue s untilth e ch un k o fdata is finishe d.
 of_an airfoil._The cooling holes are_curved and_open_at the_surface_of the leading_edge to form_oval shaped outlets whose_major dimension is_angled_relative to the leading edge.
Forming non-linear cooling holes may be more difficult to manufacture_as_compared to_linear_ones_thereby adding to the cost_of manufacturing each airfoil. U.S._Pat. No._6,379,118 to Lutum et al., for example, discloses_linear_or straight-hole cooling_holes that extend from an interior passageway of an_airfoil to its leading edge surface._The cooling holes_are_also_angled in a radially_upward direction toward the leading edge_surface.
While such linear cooling holes may_be more efficient in terms of manufacturing,_the nature and shape of the_airfoil typically constrains how large_the outlet_formed may be. The spanwise_or radial dimension_of the_outlet (i.e., the_breakout length), for example, is usually_limited by the_fact that cooling holes made by_electro-discharge_machining or by_laser_can_be difficult_to angle relative_to_the leading_edge_surface.
Accordingly, the breakout length may be_less_than desired since to increase the breakout_length, the cooling hole_would_have to be formed_at a shallow angle relative_to the leading edge surface. If,_however, the_angle is_too shallow relative to the leading edge surface, an electro-discharge device_or other machining apparatus may skip_across the leading edge_surface. This,_of_course, could possibly_damage_the airfoil,_but would not properly form the desired_cooling hole._A laser beam at too shallow_an angle, may reflect_off_the leading edge surface. The present_disclosure relates to hardware efficient fingerprinting._In particular, the present disclosure_relates_to_a pipelined hardware architecture for_computing fingerprints on high throughput data.
As_data increases rapidly,_identifying and reducing the redundancy in the_storage,_transmission, and processing of data has_become_more and more important. One of_the_common_techniques used in identifying redundant_data is comparing sketches of data_chunks to find duplication or similarity. To illustrate, Rabin_fingerprints have proved_to be effective and are_widely_used_in the detection of data duplication and similarity. To get_a sketch_for a data_chunk using Rabin fingerprints, the data is scanned using a_fixed size window, e.g., 8 bytes long,_that rolls one byte ahead every step. The data within the_window, called a “shingle,” is used to calculate_a Rabin fingerprint. This process continues until_the chunk of data_is_finished.