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S9032 (9%) (s9032-il)

S9032 (9%) - Selig S9032 (9%) symmetrical horizontal stab airfoil used on the Blackhawk R/C sailplane


Airfoil s9032-il
Details Dat file Parser  
(s9032-il) S9032 (9%)
Selig S9032 (9%) symmetrical horizontal stab airfoil used on the Blackhawk R/C sailplane
Max thickness 9% at 25% chord.
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
S9032 (9%)
    1.000000  0.000000
    0.999160  0.000010
    0.996650  0.000110
    0.992540  0.000330
    0.986880  0.000710
    0.979750  0.001250
    0.971200  0.001950
    0.961300  0.002770
    0.950090  0.003680
    0.937570  0.004650
    0.923770  0.005680
    0.908720  0.006790
    0.892470  0.007990
    0.875090  0.009280
    0.856630  0.010650
    0.837140  0.012100
    0.816710  0.013630
    0.795380  0.015230
    0.773240  0.016900
    0.750350  0.018630
    0.726780  0.020400
    0.702610  0.022220
    0.677910  0.024070
    0.652780  0.025940
    0.627290  0.027810
    0.601520  0.029650
    0.575530  0.031450
    0.549380  0.033190
    0.523170  0.034870
    0.496970  0.036470
    0.470830  0.037950
    0.444830  0.039330
    0.419040  0.040590
    0.393540  0.041720
    0.368380  0.042690
    0.343640  0.043510
    0.319370  0.044170
    0.295660  0.044650
    0.272550  0.044920
    0.250080  0.045000
    0.228330  0.044880
    0.207360  0.044550
    0.187200  0.043980
    0.167880  0.043190
    0.149470  0.042190
    0.132020  0.040970
    0.115550  0.039490
    0.100070  0.037780
    0.085630  0.035870
    0.072280  0.033750
    0.060030  0.031390
    0.048860  0.028820
    0.038810  0.026090
    0.029940  0.023200
    0.022220  0.020090
    0.015600  0.016840
    0.010110  0.013520
    0.005830  0.010180
    0.002770  0.006720
    0.000780  0.003250
    0.000000  0.000000
    0.000780 -0.003250
    0.002770 -0.006720
    0.005830 -0.010180
    0.010110 -0.013520
    0.015600 -0.016840
    0.022220 -0.020090
    0.029940 -0.023200
    0.038810 -0.026090
    0.048860 -0.028820
    0.060030 -0.031390
    0.072280 -0.033750
    0.085630 -0.035870
    0.100070 -0.037780
    0.115550 -0.039490
    0.132020 -0.040970
    0.149470 -0.042190
    0.167880 -0.043190
    0.187200 -0.043980
    0.207360 -0.044550
    0.228330 -0.044880
    0.250080 -0.045000
    0.272550 -0.044920
    0.295660 -0.044650
    0.319370 -0.044170
    0.343640 -0.043510
    0.368380 -0.042690
    0.393540 -0.041720
    0.419040 -0.040590
    0.444830 -0.039330
    0.470830 -0.037950
    0.496970 -0.036470
    0.523170 -0.034870
    0.549380 -0.033190
    0.575530 -0.031450
    0.601520 -0.029650
    0.627290 -0.027810
    0.652780 -0.025940
    0.677910 -0.024070
    0.702610 -0.022220
    0.726780 -0.020400
    0.750350 -0.018630
    0.773240 -0.016900
    0.795380 -0.015230
    0.816710 -0.013630
    0.837140 -0.012100
    0.856630 -0.010650
    0.875090 -0.009280
    0.892470 -0.007990
    0.908720 -0.006790
    0.923770 -0.005680
    0.937570 -0.004650
    0.950090 -0.003680
    0.961300 -0.002770
    0.971200 -0.001950
    0.979750 -0.001250
    0.986880 -0.000710
    0.992540 -0.000330
    0.996650 -0.000110
    0.999160 -0.000010
    1.000000  0.000000
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Polars for S9032 (9%) (s9032-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   s9032-il50,000923.5 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   s9032-il50,000525 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   s9032-il100,000932.7 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   s9032-il100,000534.2 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   s9032-il200,000943.2 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   s9032-il200,000544.9 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   s9032-il500,000960.2 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   s9032-il500,000561 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   s9032-il1,000,000974.2 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   s9032-il1,000,000574.1 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
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