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NASA SC(2)-1010 AIRFOIL (sc21010-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-1010 AIRFOIL (sc21010-il)
Reynolds number: 50,000
Max Cl/Cd: 36.06 at α=1.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc21010-il-50000-n5.txt
Download as CSV file: xf-sc21010-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-1010 AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.5031   0.10168   0.09366  -0.0419   0.9999   0.0673
 -12.250  -0.5090   0.09717   0.08923  -0.0431   0.9999   0.0669
 -12.000  -0.5173   0.09243   0.08457  -0.0444   0.9999   0.0664
 -11.750  -0.5296   0.08728   0.07951  -0.0459   0.9999   0.0659
 -11.500  -0.5488   0.08139   0.07372  -0.0478   0.9999   0.0652
 -11.250  -0.5759   0.07500   0.06742  -0.0506   0.9999   0.0643
 -11.000  -0.5996   0.06801   0.06038  -0.0559   0.9999   0.0636
 -10.500  -0.6135   0.05625   0.04807  -0.0638   0.9999   0.0636
 -10.250  -0.6046   0.05150   0.04293  -0.0670   0.9999   0.0648
 -10.000  -0.5884   0.04706   0.03796  -0.0703   0.9999   0.0672
  -9.750  -0.5655   0.04271   0.03284  -0.0739   0.9999   0.0697
  -9.500  -0.5426   0.03982   0.02969  -0.0752   0.9999   0.0716
  -9.250  -0.5195   0.03778   0.02748  -0.0760   0.9999   0.0743
  -9.000  -0.4943   0.03586   0.02525  -0.0769   0.9999   0.0788
  -8.750  -0.4664   0.03377   0.02261  -0.0780   0.9999   0.0831
  -8.500  -0.4428   0.03224   0.02113  -0.0780   0.9999   0.0867
  -8.250  -0.4173   0.03100   0.01972  -0.0783   0.9999   0.0932
  -8.000  -0.3920   0.02973   0.01828  -0.0782   0.9999   0.0993
  -7.750  -0.3670   0.02871   0.01723  -0.0781   0.9999   0.1067
  -7.500  -0.3412   0.02773   0.01620  -0.0782   0.9999   0.1165
  -7.250  -0.3142   0.02681   0.01519  -0.0785   0.9999   0.1288
  -7.000  -0.2860   0.02587   0.01433  -0.0794   0.9999   0.1465
  -6.750  -0.2549   0.02488   0.01347  -0.0810   0.9999   0.1745
  -6.500  -0.2188   0.02371   0.01270  -0.0842   0.9999   0.2294
  -6.250  -0.1814   0.02272   0.01245  -0.0875   0.9999   0.3493
  -6.000  -0.1541   0.02261   0.01271  -0.0875   0.9999   0.4489
  -5.750  -0.1307   0.02281   0.01302  -0.0864   0.9999   0.5116
  -5.500  -0.1088   0.02309   0.01331  -0.0849   0.9999   0.5569
  -5.250  -0.0883   0.02341   0.01363  -0.0830   0.9999   0.5919
  -5.000  -0.0682   0.02375   0.01395  -0.0811   0.9999   0.6232
  -4.750  -0.0522   0.02415   0.01437  -0.0781   0.9999   0.6496
  -4.500  -0.0332   0.02448   0.01466  -0.0760   0.9999   0.6754
  -4.250  -0.0150   0.02476   0.01491  -0.0738   0.9999   0.6966
  -4.000   0.0059   0.02496   0.01507  -0.0724   0.9999   0.7153
  -3.750   0.0274   0.02513   0.01519  -0.0713   0.9999   0.7322
  -3.500   0.0497   0.02529   0.01531  -0.0704   0.9999   0.7482
  -3.250   0.0725   0.02545   0.01543  -0.0698   0.9999   0.7636
  -3.000   0.0953   0.02562   0.01558  -0.0692   0.9999   0.7787
  -2.750   0.1187   0.02578   0.01573  -0.0688   0.9999   0.7934
  -2.500   0.1421   0.02596   0.01590  -0.0684   0.9999   0.8080
  -2.250   0.1656   0.02615   0.01610  -0.0682   0.9999   0.8228
  -2.000   0.1892   0.02634   0.01632  -0.0680   0.9999   0.8378
  -1.750   0.2202   0.02654   0.01654  -0.0693   0.9956   0.8528
  -1.500   0.2528   0.02672   0.01676  -0.0708   0.9898   0.8677
  -1.250   0.2872   0.02692   0.01703  -0.0727   0.9842   0.8833
  -1.000   0.3175   0.02703   0.01722  -0.0738   0.9769   0.8994
  -0.750   0.3529   0.02719   0.01748  -0.0758   0.9706   0.9175
  -0.500   0.3812   0.02719   0.01763  -0.0765   0.9611   0.9377
  -0.250   0.4111   0.02722   0.01781  -0.0776   0.9499   0.9709
   0.000   0.4521   0.02753   0.01827  -0.0809   0.9391   1.0001
   0.250   0.5004   0.02786   0.01878  -0.0854   0.9284   1.0001
   0.500   0.5470   0.02794   0.01905  -0.0891   0.9132   1.0001
   0.750   0.5915   0.02755   0.01890  -0.0915   0.8894   1.0001
   1.000   0.6499   0.02578   0.01739  -0.0939   0.8504   1.0001
   1.250   0.6916   0.02410   0.01594  -0.0932   0.8050   1.0001
   1.500   0.7200   0.02311   0.01516  -0.0910   0.7473   1.0001
   1.750   0.7796   0.02162   0.01226  -0.0904   0.4342   1.0001
   2.000   0.7883   0.02420   0.01343  -0.0878   0.2440   1.0001
   2.250   0.8071   0.02618   0.01477  -0.0870   0.1691   1.0001
   2.500   0.8309   0.02777   0.01608  -0.0868   0.1378   1.0001
   2.750   0.8575   0.02920   0.01744  -0.0868   0.1199   1.0001
   3.000   0.8868   0.03060   0.01882  -0.0872   0.1067   1.0001
   3.250   0.9196   0.03198   0.02024  -0.0880   0.0968   1.0001
   3.500   0.9541   0.03350   0.02185  -0.0889   0.0886   1.0001
   3.750   0.9871   0.03515   0.02346  -0.0898   0.0823   1.0001
   4.000   1.0216   0.03717   0.02566  -0.0907   0.0774   1.0001
   4.250   1.0515   0.03904   0.02774  -0.0911   0.0723   1.0001
   4.500   1.0803   0.04120   0.02996  -0.0915   0.0690   1.0001
   4.750   1.1077   0.04387   0.03294  -0.0915   0.0665   1.0001
   5.000   1.1306   0.04649   0.03606  -0.0907   0.0634   1.0001
   5.250   1.1511   0.04908   0.03900  -0.0898   0.0607   1.0001
   5.500   1.1700   0.05196   0.04219  -0.0888   0.0592   1.0001
   5.750   1.1863   0.05507   0.04559  -0.0877   0.0581   1.0001
   6.000   1.2007   0.05833   0.04909  -0.0865   0.0569   1.0001
   6.250   1.2056   0.06216   0.05341  -0.0841   0.0560   1.0001
   6.500   1.2040   0.06622   0.05805  -0.0811   0.0551   1.0001
   6.750   1.1981   0.07040   0.06271  -0.0782   0.0542   1.0001
   7.000   1.1882   0.07466   0.06737  -0.0753   0.0537   1.0001
   7.250   1.1737   0.07899   0.07203  -0.0724   0.0535   1.0001
   7.500   1.1526   0.08321   0.07651  -0.0694   0.0535   1.0001
   7.750   1.1294   0.08801   0.08154  -0.0675   0.0537   1.0001
   8.000   1.1045   0.09353   0.08728  -0.0673   0.0539   1.0001
   8.250   1.0784   0.10005   0.09397  -0.0689   0.0543   1.0001
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