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S9037 (9%) (s9037-il)

S9037 (9%) - Selig S9037 (9%) low Reynolds number airfoil used on the Opus R/C sailplane


Airfoil s9037-il
Details Dat file Parser  
(s9037-il) S9037 (9%)
Selig S9037 (9%) low Reynolds number airfoil used on the Opus R/C sailplane
Max thickness 9% at 28.5% chord.
Max camber 3.3% at 42.4% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
S9037 (9%)
 1.00000  0.00000
 0.99917  0.00009
 0.99670  0.00041
 0.99264  0.00099
 0.98705  0.00186
 0.97999  0.00303
 0.97153  0.00449
 0.96173  0.00623
 0.95065  0.00822
 0.93833  0.01045
 0.92483  0.01288
 0.91016  0.01553
 0.89440  0.01839
 0.87765  0.02144
 0.85998  0.02465
 0.84146  0.02797
 0.82212  0.03134
 0.80199  0.03477
 0.78117  0.03823
 0.75972  0.04168
 0.73768  0.04509
 0.71508  0.04844
 0.69201  0.05173
 0.66854  0.05491
 0.64471  0.05797
 0.62059  0.06089
 0.59623  0.06366
 0.57173  0.06624
 0.54712  0.06861
 0.52244  0.07075
 0.49776  0.07268
 0.47317  0.07436
 0.44869  0.07577
 0.42438  0.07691
 0.40030  0.07779
 0.37653  0.07839
 0.35310  0.07870
 0.33007  0.07872
 0.30750  0.07845
 0.28545  0.07788
 0.26397  0.07699
 0.24306  0.07580
 0.22280  0.07432
 0.20325  0.07255
 0.18442  0.07047
 0.16634  0.06810
 0.14905  0.06548
 0.13262  0.06261
 0.11705  0.05947
 0.10236  0.05611
 0.08858  0.05255
 0.07578  0.04880
 0.06394  0.04485
 0.05306  0.04075
 0.04316  0.03654
 0.03429  0.03225
 0.02645  0.02788
 0.01959  0.02347
 0.01375  0.01911
 0.00896  0.01483
 0.00522  0.01066
 0.00247  0.00665
 0.00072  0.00294
 0.00001 -0.00030
 0.00066 -0.00281
 0.00298 -0.00485
 0.00684 -0.00681
 0.01211 -0.00863
 0.01874 -0.01028
 0.02670 -0.01173
 0.03598 -0.01299
 0.04657 -0.01403
 0.05844 -0.01487
 0.07158 -0.01551
 0.08595 -0.01595
 0.10153 -0.01620
 0.11829 -0.01627
 0.13618 -0.01617
 0.15516 -0.01592
 0.17519 -0.01552
 0.19621 -0.01500
 0.21817 -0.01437
 0.24101 -0.01365
 0.26466 -0.01285
 0.28906 -0.01199
 0.31413 -0.01109
 0.33980 -0.01016
 0.36598 -0.00922
 0.39260 -0.00828
 0.41957 -0.00734
 0.44681 -0.00643
 0.47424 -0.00553
 0.50176 -0.00468
 0.52931 -0.00385
 0.55678 -0.00308
 0.58409 -0.00235
 0.61117 -0.00168
 0.63793 -0.00106
 0.66427 -0.00050
 0.69013  0.00000
 0.71543  0.00043
 0.74007  0.00081
 0.76399  0.00113
 0.78711  0.00140
 0.80937  0.00162
 0.83070  0.00178
 0.85104  0.00189
 0.87032  0.00194
 0.88846  0.00193
 0.90542  0.00188
 0.92112  0.00180
 0.93554  0.00169
 0.94863  0.00156
 0.96035  0.00140
 0.97065  0.00120
 0.97948  0.00097
 0.98678  0.00072
 0.99253  0.00047
 0.99667  0.00024
 0.99916  0.00007
 1.00000  0.00000
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Polars for S9037 (9%) (s9037-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   s9037-il50,000934.7 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   s9037-il50,000539.8 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   s9037-il100,000956.8 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   s9037-il100,000557.7 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   s9037-il200,000978.1 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   s9037-il200,000574.3 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   s9037-il500,0009104.8 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   s9037-il500,000595.2 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   s9037-il1,000,0009123.2 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   s9037-il1,000,0005110.1 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
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