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S8066 (10% version of S8065 w/ lower surface aerodynamically similar) (s8066-il)

S8066 (10% version of S8065 w/ lower surface aerodynamically similar) - Selig airfoil for Q-40 pylon racing (10%).


Airfoil s8066-il
Details Dat file Parser  
(s8066-il) S8066 (10% version of S8065 w/ lower surface aerodynamically similar)
Selig airfoil for Q-40 pylon racing (10%).
Max thickness 10% at 37.7% chord.
Max camber 0.8% at 56.3% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
S8066 (10% version of S8065 w/ lower surface aerodynamically similar)
    1.000000000000000000  0.000000000000000000
    0.998057840676878200  0.000166937137092193
    0.992416288358743700  0.000736101176910097
    0.983245987259313700  0.001707160029229792
    0.970646747337505600  0.003152504369279306
    0.954818541144353400  0.005146245183049103
    0.935983110880433600  0.007707809325103161
    0.914386897207902500  0.010836188874850960
    0.890294701271966600  0.014493097950599640
    0.863985843396096700  0.018611364651165420
    0.835747980435427700  0.023083453218744910
    0.805873552569857300  0.027761439717320720
    0.774651388414176800  0.032349045000253510
    0.742075285453536200  0.036620241395957260
    0.708130554465947700  0.040592132118529360
    0.673060536855025600  0.044282002220962890
    0.637083548729503900  0.047644340324827030
    0.600406080795886900  0.050640855949782890
    0.563229093923920400  0.053221357453983410
    0.525760643828765200  0.055337432323898070
    0.488207667152002000  0.056953607361102950
    0.450758802091959300  0.058050934904195550
    0.413593568949964700  0.058608081621481900
    0.376901091069881100  0.058621665900739330
    0.340872604479462600  0.058118342811318250
    0.305707681159613900  0.057129170688947360
    0.271613337606657100  0.055675760827435740
    0.238790640113367100  0.053783450602283430
    0.207435534132227100  0.051474059218642570
    0.177732390978254100  0.048771938390013110
    0.149855484388894100  0.045703538686043460
    0.123968888850612100  0.042300272293876770
    0.100227078657608300  0.038592574793425570
    0.078767791290352160  0.034613195258580670
    0.059716732851738290  0.030401400719312060
    0.043191411615824290  0.025997272168372010
    0.029320663689782260  0.021415784908867110
    0.018142208630512640  0.016669739071798080
    0.009626213537717643  0.011797414319730890
    0.003779424592163627  0.006866449528923698
    0.000504861490119302  0.002159251412195534
    0.000400153232463452 -0.001904247349762149
    0.003742396145787086 -0.005836603062247162
    0.010009005739912700 -0.010032318419174010
    0.019043328683611140 -0.014143485494395680
    0.030834186950634560 -0.018079102914508270
    0.045375275153131880 -0.021774640298329360
    0.062595493596290910 -0.025181227413669800
    0.082416556293053330 -0.028286404890973540
    0.104739175721816000 -0.031088362951255650
    0.129441762181518300 -0.033576392808939070
    0.156373007718436200 -0.035751357458343810
    0.185362001148172600 -0.037607321413554480
    0.216222807750386800 -0.039132846744997650
    0.248762958747129900 -0.040310345356248400
    0.282780529366068300 -0.041126296955429410
    0.318064339246098200 -0.041555758155484480
    0.354417087125452500 -0.041571162248819320
    0.391645197234607700 -0.041167815748720730
    0.429543776639067400 -0.040335757653581360
    0.467916685988158000 -0.039075173658798740
    0.506586195150717200 -0.037436100578794230
    0.545334272065676700 -0.035482115857896970
    0.583889632897935000 -0.033264821388625520
    0.621984839696719400 -0.030799216869729770
    0.659336570518512800 -0.028058481549376570
    0.695864758616024300 -0.024914276343846020
    0.731570700564536800 -0.021499489286928560
    0.766223587084074300 -0.018119141500758550
    0.799506767418079400 -0.014910851976491940
    0.831114349121348900 -0.011966303940033010
    0.860749475033995100 -0.009347501844977414
    0.888128005630994500 -0.007087470215592590
    0.912982886897509800 -0.005197570586413698
    0.935067371759332900 -0.003664571237356523
    0.954155536243004000 -0.002449116895450627
    0.970080315650033300 -0.001463440916806641
    0.982789320394193000 -0.000667762033907935
    0.992188134694531200 -0.000159936244795328
    0.998019447354635500  0.000009663562748016
    1.000000000000000000  0.000000000000000004
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Polars for S8066 (10% version of S8065 w/ lower surface aerodynamically similar) (s8066-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   s8066-il50,000932.6 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   s8066-il50,000531.5 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   s8066-il100,000947.9 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   s8066-il100,000544.6 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   s8066-il200,000964.7 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   s8066-il200,000554.1 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   s8066-il500,000975 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   s8066-il500,000561.6 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   s8066-il1,000,000981.2 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   s8066-il1,000,000573.2 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
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