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S9000 (9%) (s9000-il)

S9000 (9%) - Selig S9000 (9%) low Reynolds number airfoil used on the Blackhawk R/C sailplane


Airfoil s9000-il
Details Dat file Parser  
(s9000-il) S9000 (9%)
Selig S9000 (9%) low Reynolds number airfoil used on the Blackhawk R/C sailplane
Max thickness 9% at 28.2% chord.
Max camber 2.1% at 44.8% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
S9000 (9%)
    1.000000  0.000000
    0.999170  0.000110
    0.996710  0.000500
    0.992700  0.001210
    0.987230  0.002250
    0.980400  0.003610
    0.972290  0.005230
    0.962940  0.007050
    0.952400  0.009000
    0.940650  0.011030
    0.927680  0.013140
    0.913520  0.015360
    0.898220  0.017680
    0.881840  0.020100
    0.864430  0.022610
    0.846060  0.025200
    0.826770  0.027850
    0.806640  0.030560
    0.785740  0.033310
    0.764120  0.036080
    0.741850  0.038850
    0.719020  0.041600
    0.695660  0.044280
    0.671850  0.046910
    0.647650  0.049460
    0.623130  0.051910
    0.598360  0.054220
    0.573380  0.056410
    0.548280  0.058450
    0.523120  0.060330
    0.497960  0.062020
    0.472860  0.063510
    0.447880  0.064810
    0.423110  0.065900
    0.398590  0.066740
    0.374360  0.067350
    0.350500  0.067720
    0.327090  0.067850
    0.304150  0.067710
    0.281730  0.067300
    0.259890  0.066650
    0.238710  0.065730
    0.218200  0.064540
    0.198410  0.063080
    0.179390  0.061380
    0.161200  0.059420
    0.143860  0.057190
    0.127380  0.054720
    0.111800  0.052040
    0.097190  0.049130
    0.083550  0.045990
    0.070870  0.042650
    0.059190  0.039160
    0.048560  0.035530
    0.038960  0.031740
    0.030390  0.027850
    0.022870  0.023920
    0.016430  0.019970
    0.011080  0.015970
    0.006750  0.012020
    0.003450  0.008200
    0.001230  0.004630
    0.000130  0.001360
    0.000200 -0.001390
    0.002030 -0.003680
    0.005370 -0.006000
    0.010060 -0.008270
    0.016060 -0.010420
    0.023360 -0.012430
    0.031940 -0.014310
    0.041770 -0.016030
    0.052840 -0.017580
    0.065120 -0.018970
    0.078590 -0.020180
    0.093220 -0.021220
    0.108960 -0.022080
    0.125800 -0.022760
    0.143700 -0.023260
    0.162600 -0.023600
    0.182460 -0.023780
    0.203250 -0.023790
    0.224890 -0.023670
    0.247350 -0.023400
    0.270550 -0.023010
    0.294450 -0.022490
    0.318960 -0.021880
    0.344030 -0.021170
    0.369580 -0.020370
    0.395530 -0.019510
    0.421830 -0.018580
    0.448380 -0.017590
    0.475100 -0.016570
    0.501930 -0.015510
    0.528770 -0.014420
    0.555530 -0.013310
    0.582150 -0.012170
    0.608530 -0.010990
    0.634590 -0.009770
    0.660300 -0.008440
    0.685670 -0.007070
    0.710620 -0.005700
    0.735070 -0.004380
    0.758930 -0.003130
    0.782120 -0.001970
    0.804570 -0.000920
    0.826180  0.000000
    0.846870  0.000790
    0.866560  0.001420
    0.885180  0.001910
    0.902650  0.002240
    0.918890  0.002420
    0.933820  0.002450
    0.947380  0.002340
    0.959500  0.002120
    0.970110  0.001810
    0.979170  0.001430
    0.986630  0.001040
    0.992470  0.000650
    0.996650  0.000320
    0.999160  0.000090
    1.000000  0.000000
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Polars for S9000 (9%) (s9000-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   s9000-il50,000934.7 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   s9000-il50,000537.9 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   s9000-il100,000953.3 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   s9000-il100,000552.7 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   s9000-il200,000971 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   s9000-il200,000566.5 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   s9000-il500,000993 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   s9000-il500,000584.4 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   s9000-il1,000,0009108.2 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   s9000-il1,000,000597.3 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
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