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S9033 (7.5%) (s9033-il)

S9033 (7.5%) - Selig S9033 (7.5%) symmetrical vertical stab airfoil used on the Blackhawk R/C sailplane


Airfoil s9033-il
Details Dat file Parser  
(s9033-il) S9033 (7.5%)
Selig S9033 (7.5%) symmetrical vertical stab airfoil used on the Blackhawk R/C sailplane
Max thickness 7.5% at 22.8% chord.
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
S9033 (7.5%)
    1.000000  0.000000
    0.999190  0.000010
    0.996780  0.000080
    0.992820  0.000250
    0.987340  0.000530
    0.980410  0.000940
    0.972090  0.001470
    0.962420  0.002090
    0.951430  0.002770
    0.939140  0.003490
    0.925570  0.004260
    0.910760  0.005090
    0.894750  0.005980
    0.877590  0.006930
    0.859340  0.007950
    0.840060  0.009030
    0.819800  0.010170
    0.798640  0.011370
    0.776630  0.012630
    0.753840  0.013930
    0.730340  0.015290
    0.706200  0.016690
    0.681510  0.018150
    0.656340  0.019630
    0.630780  0.021130
    0.604910  0.022640
    0.578780  0.024130
    0.552490  0.025600
    0.526090  0.027050
    0.499690  0.028440
    0.473330  0.029780
    0.447100  0.031050
    0.421080  0.032240
    0.395330  0.033340
    0.369930  0.034330
    0.344930  0.035210
    0.320420  0.035970
    0.296470  0.036590
    0.273120  0.037050
    0.250430  0.037350
    0.228470  0.037490
    0.207300  0.037460
    0.186970  0.037220
    0.167510  0.036800
    0.148980  0.036180
    0.131440  0.035360
    0.114900  0.034300
    0.099390  0.033020
    0.084930  0.031540
    0.071590  0.029840
    0.059370  0.027900
    0.048240  0.025760
    0.038250  0.023440
    0.029450  0.020940
    0.021820  0.018210
    0.015280  0.015320
    0.009880  0.012350
    0.005680  0.009340
    0.002690  0.006180
    0.000760  0.002990
    0.000000  0.000000
    0.000760 -0.002990
    0.002690 -0.006180
    0.005680 -0.009340
    0.009880 -0.012350
    0.015280 -0.015320
    0.021820 -0.018210
    0.029450 -0.020940
    0.038250 -0.023440
    0.048240 -0.025760
    0.059370 -0.027900
    0.071590 -0.029840
    0.084930 -0.031540
    0.099390 -0.033020
    0.114900 -0.034300
    0.131440 -0.035360
    0.148980 -0.036180
    0.167510 -0.036800
    0.186970 -0.037220
    0.207300 -0.037460
    0.228470 -0.037490
    0.250430 -0.037350
    0.273120 -0.037050
    0.296470 -0.036590
    0.320420 -0.035970
    0.344930 -0.035210
    0.369930 -0.034330
    0.395330 -0.033340
    0.421080 -0.032240
    0.447100 -0.031050
    0.473330 -0.029780
    0.499690 -0.028440
    0.526090 -0.027050
    0.552490 -0.025600
    0.578780 -0.024130
    0.604910 -0.022640
    0.630780 -0.021130
    0.656340 -0.019630
    0.681510 -0.018150
    0.706200 -0.016690
    0.730340 -0.015290
    0.753840 -0.013930
    0.776630 -0.012630
    0.798640 -0.011370
    0.819800 -0.010170
    0.840060 -0.009030
    0.859340 -0.007950
    0.877590 -0.006930
    0.894750 -0.005980
    0.910760 -0.005090
    0.925570 -0.004260
    0.939140 -0.003490
    0.951430 -0.002770
    0.962420 -0.002090
    0.972090 -0.001470
    0.980410 -0.000940
    0.987340 -0.000530
    0.992820 -0.000250
    0.996780 -0.000080
    0.999190 -0.000010
    1.000000  0.000000
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Polars for S9033 (7.5%) (s9033-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   s9033-il50,000921.7 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   s9033-il50,000523.5 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   s9033-il100,000929.5 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   s9033-il100,000532.3 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   s9033-il200,000939.6 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   s9033-il200,000542.9 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   s9033-il500,000956.9 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   s9033-il500,000558.9 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   s9033-il1,000,000970.7 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   s9033-il1,000,000572 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
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