Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

S9026 (9.5%) (s9026-il)

S9026 (9.5%) - Selig S9026 (9.5%) symmetrical horizontal stab airfoil used on the Opus R/C sailplane


Airfoil s9026-il
Details Dat file Parser  
(s9026-il) S9026 (9.5%)
Selig S9026 (9.5%) symmetrical horizontal stab airfoil used on the Opus R/C sailplane
Max thickness 9.5% at 27.3% chord.
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
  S9026 (9.5%)
       1.00000     0.00000
       0.99915     0.00002
       0.99661     0.00011
       0.99244     0.00034
       0.98671     0.00074
       0.97949     0.00132
       0.97085     0.00206
       0.96084     0.00294
       0.94950     0.00393
       0.93686     0.00499
       0.92293     0.00614
       0.90775     0.00739
       0.89138     0.00875
       0.87389     0.01021
       0.85532     0.01177
       0.83576     0.01343
       0.81526     0.01519
       0.79390     0.01702
       0.77175     0.01892
       0.74888     0.02088
       0.72538     0.02288
       0.70131     0.02489
       0.67675     0.02689
       0.65174     0.02887
       0.62636     0.03082
       0.60070     0.03273
       0.57482     0.03457
       0.54879     0.03634
       0.52267     0.03803
       0.49656     0.03962
       0.47052     0.04109
       0.44460     0.04244
       0.41889     0.04365
       0.39346     0.04472
       0.36837     0.04563
       0.34368     0.04637
       0.31947     0.04695
       0.29581     0.04733
       0.27273     0.04750
       0.25030     0.04747
       0.22857     0.04723
       0.20762     0.04678
       0.18748     0.04609
       0.16817     0.04517
       0.14976     0.04403
       0.13230     0.04267
       0.11583     0.04106
       0.10033     0.03922
       0.08587     0.03717
       0.07251     0.03491
       0.06023     0.03242
       0.04903     0.02972
       0.03895     0.02686
       0.03005     0.02384
       0.02230     0.02062
       0.01564     0.01725
       0.01012     0.01383
       0.00583     0.01038
       0.00274     0.00684
       0.00073     0.00329
       0.00000     0.00000
       0.00073    -0.00329
       0.00274    -0.00684
       0.00583    -0.01038
       0.01012    -0.01383
       0.01564    -0.01725
       0.02230    -0.02062
       0.03005    -0.02384
       0.03895    -0.02686
       0.04903    -0.02972
       0.06023    -0.03242
       0.07251    -0.03491
       0.08587    -0.03717
       0.10033    -0.03922
       0.11583    -0.04106
       0.13230    -0.04267
       0.14976    -0.04403
       0.16817    -0.04517
       0.18748    -0.04609
       0.20762    -0.04678
       0.22857    -0.04723
       0.25030    -0.04747
       0.27273    -0.04750
       0.29581    -0.04733
       0.31947    -0.04695
       0.34368    -0.04637
       0.36837    -0.04563
       0.39346    -0.04472
       0.41889    -0.04365
       0.44460    -0.04244
       0.47052    -0.04109
       0.49656    -0.03962
       0.52267    -0.03803
       0.54879    -0.03634
       0.57482    -0.03457
       0.60070    -0.03273
       0.62636    -0.03082
       0.65174    -0.02887
       0.67675    -0.02689
       0.70131    -0.02489
       0.72538    -0.02288
       0.74888    -0.02088
       0.77175    -0.01892
       0.79390    -0.01702
       0.81526    -0.01519
       0.83576    -0.01343
       0.85532    -0.01177
       0.87389    -0.01021
       0.89138    -0.00875
       0.90775    -0.00739
       0.92293    -0.00614
       0.93686    -0.00499
       0.94950    -0.00393
       0.96084    -0.00294
       0.97085    -0.00206
       0.97949    -0.00132
       0.98671    -0.00074
       0.99244    -0.00034
       0.99661    -0.00011
       0.99915    -0.00002
       1.00000     0.00000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

Prandtl-D tip - NASA PreliminaryPreviewDetails
RAF 27 AIRFOILPreviewDetails
LWK 79-100PreviewDetails
RAE 100 AIRFOILPreviewDetails
EH 0.0/9.0PreviewDetails
Joukovsky f=0% t=9%PreviewDetails
E230 (9.96%)PreviewDetails
S9032 (9%)PreviewDetails
WORTMANN FX 76-100PreviewDetails
EPPLER EA 6(-1)-009 AIRFOILPreviewDetails

Polars for S9026 (9.5%) (s9026-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   s9026-il50,000924.2 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   s9026-il50,000525.4 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   s9026-il100,000933.8 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   s9026-il100,000534.6 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   s9026-il200,000944.3 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   s9026-il200,000545.3 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   s9026-il500,000960.9 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   s9026-il500,000561.5 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   s9026-il1,000,000975.1 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   s9026-il1,000,000574.6 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit