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S1221 w/ 4 deg flap (s1221-flap-il)

S1221 w/ 4 deg flap - Selig S1221 airfoil with 4 deg flap


Airfoil s1221-flap-il
Details Dat file Parser  
(s1221-flap-il) S1221 w/ 4 deg flap
Selig S1221 airfoil with 4 deg flap
Max thickness 12.1% at 21.8% chord.
Max camber 5.3% at 52.9% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
S1221  w/ 4 deg flap
0.99927 -0.00338
0.99761 -0.00254
0.99306  0.00001
0.98626  0.00377
0.97730  0.00799
0.96571  0.01227
0.95129  0.01679
0.94627  0.01824
0.87364  0.03696
0.83704  0.04523
0.82224  0.04831
0.80740  0.05112
0.79250  0.05360
0.77754  0.05572
0.72514  0.06224
0.65074  0.07145
0.64181  0.07259
0.60456  0.07717
0.56677  0.08157
0.52865  0.08577
0.49051  0.08975
0.45264  0.09349
0.41537  0.09693
0.37902  0.09992
0.34385  0.10232
0.31005  0.10396
0.27776  0.10469
0.24715  0.10447
0.21836  0.10298
0.19125  0.10011
0.16569  0.09601
0.14166  0.09077
0.11918  0.08461
0.09838  0.07771
0.07937  0.07022
0.06223  0.06222
0.04705  0.05386
0.03388  0.04528
0.02281  0.03663
0.01391  0.02808
0.00733  0.01969
0.00297  0.01152
0.00065  0.00384
0.00037 -0.00287
0.00271 -0.00774
0.00859 -0.01117
0.01809 -0.01422
0.03068 -0.01687
0.04619 -0.01909
0.06442 -0.02087
0.08523 -0.02216
0.10841 -0.02290
0.13379 -0.02304
0.16116 -0.02248
0.19026 -0.02101
0.22124 -0.01813
0.25456 -0.01393
0.29025 -0.00894
0.32811 -0.00346
0.36788  0.00227
0.40929  0.00801
0.45202  0.01360
0.49574  0.01880
0.54006  0.02346
0.58459  0.02742
0.62895  0.03058
0.65126  0.03183
0.72628  0.03528
0.77128  0.03648
0.78630  0.03650
0.80131  0.03610
0.81631  0.03527
0.83128  0.03399
0.87548  0.02860
0.94938  0.01434
0.96794  0.00915
0.98244  0.00397
0.99211 -0.00014
0.99753 -0.00259
0.99925 -0.00338
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Polars for S1221 w/ 4 deg flap (s1221-flap-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   s1221-flap-il50,000931 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   s1221-flap-il50,000539.2 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   s1221-flap-il100,000948.3 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   s1221-flap-il100,000556.4 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   s1221-flap-il200,000969.3 at α=9.75°Mach=0 Ncrit=9Xfoil predictionDetails
   s1221-flap-il200,000576.3 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   s1221-flap-il500,0009104.6 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   s1221-flap-il500,0005106.5 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   s1221-flap-il1,000,0009133.8 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   s1221-flap-il1,000,0005129.5 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
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