S8065 (11% version of S8064) (s8065-il)
S8065 (11% version of S8064) - Selig airfoil for Q-40 pylon racing (11%).
| Details | Dat file | Parser | |
|
(s8065-il) S8065 (11% version of S8064) Selig airfoil for Q-40 pylon racing (11%). Max thickness 11% at 37.8% chord. Max camber 1.1% at 56.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
S8065 (11% version of S8064)
1.000000000000000000 0.000000000000000000
0.997993446185353500 0.000130811143500576
0.992120253827858500 0.000648855829965359
0.982560757808007100 0.001649265266565549
0.969470785111610500 0.003248120022319079
0.953091018839729800 0.005539948722110745
0.933692440438248500 0.008559970954169636
0.911573206720229500 0.012305217178092380
0.887049593574342100 0.016722465320307010
0.860448817703657600 0.021713525746054400
0.832100105182719600 0.027125281982624930
0.802327541350492800 0.032745884515611410
0.771461468721389900 0.038191456467464470
0.739364032839643000 0.043099196978347680
0.705867124336291100 0.047496175047492290
0.671223087933386800 0.051503637686130350
0.635651228772872100 0.055096250743591880
0.599356374311958400 0.058244507745990310
0.562540327506452300 0.060902656670060410
0.525412054459625100 0.063031440715143820
0.488175880025791300 0.064604202196046630
0.451018150627321500 0.065602106342505060
0.414120232672516500 0.066002980976104590
0.377671628557788000 0.065810184898614120
0.341859321754045000 0.065052518633958320
0.306879443495999200 0.063764173426503510
0.272938389525968300 0.061971822234953300
0.240236199932116400 0.059704693805376210
0.208967271787325900 0.056988981021670270
0.179314874520905800 0.053854515652283240
0.151453252607483100 0.050333239885510120
0.125546645934405500 0.046461822633340390
0.101749367297932200 0.042275968248952310
0.080199084935582920 0.037815310839931210
0.061022939263114530 0.033125970468901500
0.044340073838314400 0.028254618415642290
0.030278750885406990 0.023237200132818140
0.018886988472003760 0.018086935813106030
0.010155978985443510 0.012834319451278800
0.004107018662571682 0.007566208716775728
0.000646005149050111 0.002533751850206041
0.000317305124873490 -0.001759655920030518
0.003478065414392439 -0.005841551016872853
0.009658692195495977 -0.010229870203694930
0.018626460148509990 -0.014558849261080630
0.030372275245346030 -0.018719454442779120
0.044882542651190520 -0.022634039186168460
0.062078258938538470 -0.026259726942717550
0.081881885564776710 -0.029582742697880410
0.104195084088463100 -0.032595891466399000
0.128893357330598000 -0.035285301807152790
0.155824611427130000 -0.037651064424792120
0.184818515012434100 -0.039685762243936630
0.215688362938107800 -0.041377650120911770
0.248240448135168900 -0.042708311083793540
0.282271719146788600 -0.043663175631764720
0.317570060249772200 -0.044216322387187220
0.353937024770963400 -0.044339761347205520
0.391177404913803600 -0.044027752558794460
0.429082395421576500 -0.043268031629888480
0.467455891409037800 -0.042063676179363250
0.506121310618604900 -0.040456051085759100
0.544861681056884400 -0.038502841063917010
0.583408140717401600 -0.036261987650680670
0.621492783639211900 -0.033749109561244770
0.658833591251356300 -0.030943598854365060
0.695330203156913700 -0.027700343754464280
0.730996395498632300 -0.024137046831734080
0.765632392092356900 -0.020573829589703380
0.798917222729626100 -0.017161001071971070
0.830542222261064500 -0.013997276597566710
0.860207358743468800 -0.011150194673557670
0.887625016401134900 -0.008656764763226560
0.912524529935530300 -0.006531673974570347
0.934655449683318200 -0.004763536039899971
0.953787287593407700 -0.003312806807577075
0.969755572684033700 -0.002082763468658889
0.982533002695512700 -0.001038425611298955
0.992036934495929800 -0.000321373691605693
0.997972587516476600 -0.000026896364049739
0.999999999999999800 -0.000000000000000039
|
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for S8065 (11% version of S8064) (s8065-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s8065-il | 50,000 | 9 | 31.8 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8065-il | 50,000 | 5 | 31.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8065-il | 100,000 | 9 | 49.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8065-il | 100,000 | 5 | 46.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8065-il | 200,000 | 9 | 69 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8065-il | 200,000 | 5 | 57.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8065-il | 500,000 | 9 | 80.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8065-il | 500,000 | 5 | 64.3 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8065-il | 1,000,000 | 9 | 88.8 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8065-il | 1,000,000 | 5 | 74.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||