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S1223 (s1223-il)

S1223 - Selig S1223 high lift low Reynolds number airfoil


Airfoil s1223-il
Details Dat file Parser  
(s1223-il) S1223
Selig S1223 high lift low Reynolds number airfoil
Max thickness 12.1% at 19.8% chord.
Max camber 8.1% at 49% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
  S1223
  1.00000     0.00000
  0.99838     0.00126
  0.99417     0.00494
  0.98825     0.01037
  0.98075     0.01646
  0.97111     0.02250
  0.95884     0.02853
  0.94389     0.03476
  0.92639     0.04116
  0.90641     0.04768
  0.88406     0.05427
  0.85947     0.06089
  0.83277     0.06749
  0.80412     0.07402
  0.77369     0.08044
  0.74166     0.08671
  0.70823     0.09277
  0.67360     0.09859
  0.63798     0.10412
  0.60158     0.10935
  0.56465     0.11425
  0.52744     0.11881
  0.49025     0.12303
  0.45340     0.12683
  0.41721     0.13011
  0.38193     0.13271
  0.34777     0.13447
  0.31488     0.13526
  0.28347     0.13505
  0.25370     0.13346
  0.22541     0.13037
  0.19846     0.12594
  0.17286     0.12026
  0.14863     0.11355
  0.12591     0.10598
  0.10482     0.09770
  0.08545     0.08879
  0.06789     0.07940
  0.05223     0.06965
  0.03855     0.05968
  0.02694     0.04966
  0.01755     0.03961
  0.01028     0.02954
  0.00495     0.01969
  0.00155     0.01033
  0.00005     0.00178
  0.00044    -0.00561
  0.00264    -0.01120
  0.00789    -0.01427
  0.01718    -0.01550
  0.03006    -0.01584
  0.04627    -0.01532
  0.06561    -0.01404
  0.08787    -0.01202
  0.11282    -0.00925
  0.14020    -0.00563
  0.17006    -0.00075
  0.20278     0.00535
  0.23840     0.01213
  0.27673     0.01928
  0.31750     0.02652
  0.36044     0.03358
  0.40519     0.04021
  0.45139     0.04618
  0.49860     0.05129
  0.54639     0.05534
  0.59428     0.05820
  0.64176     0.05976
  0.68832     0.05994
  0.73344     0.05872
  0.77660     0.05612
  0.81729     0.05219
  0.85500     0.04706
  0.88928     0.04088
  0.91966     0.03387
  0.94573     0.02624
  0.96693     0.01822
  0.98255     0.01060
  0.99268     0.00468
  0.99825     0.00115
  1.00000     0.00000
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Polars for S1223 (s1223-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   s1223-il50,000933.1 at α=2°Mach=0 Ncrit=9Xfoil predictionDetails
   s1223-il50,000542.3 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   s1223-il100,000954.5 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   s1223-il100,000559.2 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   s1223-il200,000973.6 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   s1223-il200,000575.3 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   s1223-il500,000998.8 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   s1223-il500,000597.4 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   s1223-il1,000,0009121.4 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   s1223-il1,000,0005120 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
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