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NASA SC(2)-0414 AIRFOIL (sc20414-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0414 AIRFOIL (sc20414-il)
Reynolds number: 100,000
Max Cl/Cd: 30.52 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20414-il-100000-n5.txt
Download as CSV file: xf-sc20414-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0414 AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.250  -0.8357   0.08888   0.08211  -0.0455   1.0000   0.0512
 -14.000  -0.8858   0.07766   0.07059  -0.0522   1.0000   0.0510
 -13.750  -0.9215   0.07006   0.06268  -0.0558   1.0000   0.0511
 -13.500  -0.9495   0.06415   0.05645  -0.0577   1.0000   0.0514
 -13.250  -0.9731   0.05922   0.05117  -0.0586   1.0000   0.0518
 -13.000  -0.9699   0.05702   0.04895  -0.0584   1.0000   0.0524
 -12.750  -0.9676   0.05489   0.04674  -0.0582   1.0000   0.0531
 -12.500  -0.9671   0.05265   0.04441  -0.0577   1.0000   0.0539
 -12.250  -0.9677   0.05036   0.04198  -0.0570   1.0000   0.0547
 -12.000  -0.9687   0.04810   0.03954  -0.0560   1.0000   0.0555
 -11.750  -0.9691   0.04593   0.03717  -0.0547   1.0000   0.0564
 -11.500  -0.9689   0.04386   0.03487  -0.0530   1.0000   0.0574
 -11.250  -0.9664   0.04182   0.03254  -0.0515   1.0000   0.0585
 -11.000  -0.9542   0.04044   0.03113  -0.0505   1.0000   0.0596
 -10.750  -0.9418   0.03929   0.02997  -0.0494   1.0000   0.0608
 -10.500  -0.9297   0.03809   0.02871  -0.0483   1.0000   0.0623
 -10.250  -0.9172   0.03679   0.02728  -0.0471   1.0000   0.0640
 -10.000  -0.9038   0.03545   0.02571  -0.0457   1.0000   0.0658
  -9.750  -0.8879   0.03431   0.02455  -0.0445   1.0000   0.0673
  -9.500  -0.8724   0.03338   0.02366  -0.0432   1.0000   0.0689
  -9.250  -0.8570   0.03247   0.02271  -0.0420   1.0000   0.0711
  -9.000  -0.8411   0.03153   0.02165  -0.0406   1.0000   0.0736
  -8.750  -0.8248   0.03061   0.02067  -0.0392   1.0000   0.0758
  -8.500  -0.8087   0.02980   0.01993  -0.0379   1.0000   0.0779
  -8.250  -0.7924   0.02904   0.01916  -0.0366   1.0000   0.0807
  -8.000  -0.7755   0.02831   0.01832  -0.0352   1.0000   0.0839
  -7.750  -0.7592   0.02754   0.01760  -0.0338   1.0000   0.0866
  -7.500  -0.7424   0.02685   0.01696  -0.0326   1.0000   0.0898
  -7.250  -0.7249   0.02621   0.01628  -0.0313   1.0000   0.0938
  -7.000  -0.7075   0.02552   0.01562  -0.0302   1.0000   0.0976
  -6.750  -0.6895   0.02489   0.01504  -0.0292   1.0000   0.1020
  -6.500  -0.6704   0.02435   0.01445  -0.0283   1.0000   0.1073
  -6.250  -0.6513   0.02368   0.01390  -0.0276   1.0000   0.1127
  -6.000  -0.6309   0.02316   0.01338  -0.0270   1.0000   0.1196
  -5.750  -0.6099   0.02258   0.01289  -0.0267   1.0000   0.1274
  -5.500  -0.5874   0.02208   0.01243  -0.0265   0.9999   0.1376
  -5.250  -0.5531   0.02146   0.01191  -0.0287   0.9965   0.1528
  -5.000  -0.5180   0.02081   0.01144  -0.0312   0.9934   0.1755
  -4.750  -0.4834   0.02008   0.01095  -0.0336   0.9898   0.2116
  -4.500  -0.4473   0.01910   0.01039  -0.0369   0.9866   0.2779
  -4.250  -0.4097   0.01794   0.01004  -0.0405   0.9842   0.4055
  -4.000  -0.3844   0.01850   0.01130  -0.0386   0.9799   0.5130
  -3.750  -0.3545   0.01896   0.01182  -0.0384   0.9743   0.5627
  -3.500  -0.3177   0.01923   0.01201  -0.0402   0.9703   0.5943
  -3.250  -0.2840   0.01968   0.01240  -0.0410   0.9663   0.6148
  -3.000  -0.2535   0.02006   0.01271  -0.0413   0.9605   0.6306
  -2.750  -0.2181   0.02040   0.01298  -0.0427   0.9564   0.6458
  -2.500  -0.1911   0.02109   0.01368  -0.0412   0.9517   0.6546
  -2.250  -0.1641   0.02157   0.01414  -0.0405   0.9455   0.6670
  -2.000  -0.1318   0.02211   0.01466  -0.0408   0.9412   0.6820
  -1.750  -0.1089   0.02283   0.01543  -0.0381   0.9363   0.6888
  -1.500  -0.0777   0.02288   0.01543  -0.0392   0.9303   0.6993
  -1.250  -0.0460   0.02294   0.01549  -0.0397   0.9260   0.7029
  -1.000  -0.0120   0.02302   0.01556  -0.0405   0.9229   0.7066
  -0.750   0.0132   0.02306   0.01561  -0.0400   0.9151   0.7115
  -0.500   0.0523   0.02284   0.01537  -0.0428   0.9103   0.7171
  -0.250   0.0926   0.02260   0.01512  -0.0456   0.9067   0.7205
   0.000   0.1191   0.02255   0.01511  -0.0451   0.8980   0.7227
   0.250   0.1552   0.02231   0.01490  -0.0463   0.8908   0.7251
   0.500   0.1879   0.02207   0.01468  -0.0469   0.8806   0.7280
   0.750   0.2300   0.02156   0.01419  -0.0489   0.8702   0.7313
   1.000   0.2667   0.02102   0.01365  -0.0502   0.8531   0.7349
   1.250   0.3065   0.02040   0.01301  -0.0521   0.8335   0.7381
   1.500   0.3352   0.02007   0.01270  -0.0514   0.8131   0.7396
   1.750   0.3623   0.01983   0.01248  -0.0506   0.7902   0.7415
   2.000   0.3900   0.01961   0.01227  -0.0499   0.7646   0.7438
   2.250   0.4194   0.01939   0.01205  -0.0496   0.7361   0.7463
   2.500   0.4486   0.01923   0.01185  -0.0495   0.6986   0.7487
   2.750   0.4790   0.01911   0.01155  -0.0495   0.6367   0.7512
   3.000   0.5070   0.01936   0.01121  -0.0491   0.5155   0.7539
   3.250   0.5282   0.02019   0.01131  -0.0482   0.3894   0.7565
   3.500   0.5467   0.02097   0.01164  -0.0466   0.3066   0.7584
   3.750   0.5676   0.02163   0.01198  -0.0455   0.2469   0.7606
   4.000   0.5905   0.02223   0.01233  -0.0449   0.2072   0.7629
   4.250   0.6154   0.02274   0.01269  -0.0447   0.1803   0.7653
   4.500   0.6412   0.02326   0.01309  -0.0447   0.1613   0.7681
   4.750   0.6687   0.02377   0.01353  -0.0452   0.1468   0.7711
   5.000   0.6956   0.02430   0.01400  -0.0454   0.1356   0.7737
   5.250   0.7183   0.02483   0.01447  -0.0447   0.1268   0.7754
   5.500   0.7423   0.02533   0.01501  -0.0441   0.1192   0.7773
   5.750   0.7657   0.02593   0.01556  -0.0436   0.1127   0.7793
   6.000   0.7908   0.02650   0.01617  -0.0433   0.1065   0.7816
   6.250   0.8158   0.02712   0.01679  -0.0431   0.1013   0.7843
   6.500   0.8421   0.02784   0.01752  -0.0433   0.0965   0.7873
   6.750   0.8697   0.02854   0.01824  -0.0437   0.0917   0.7902
   7.000   0.8915   0.02929   0.01894  -0.0429   0.0884   0.7921
   7.250   0.9155   0.03002   0.01981  -0.0423   0.0846   0.7940
   7.500   0.9393   0.03078   0.02061  -0.0419   0.0811   0.7962
   7.750   0.9631   0.03165   0.02143  -0.0417   0.0785   0.7986
   8.000   0.9883   0.03261   0.02256  -0.0415   0.0754   0.8011
   8.250   1.0133   0.03356   0.02362  -0.0415   0.0724   0.8039
   8.500   1.0390   0.03454   0.02460  -0.0418   0.0702   0.8070
   8.750   1.0601   0.03562   0.02576  -0.0409   0.0683   0.8092
   9.000   1.0807   0.03681   0.02721  -0.0400   0.0659   0.8117
   9.250   1.1013   0.03789   0.02842  -0.0392   0.0638   0.8144
   9.500   1.1223   0.03890   0.02947  -0.0387   0.0622   0.8170
   9.750   1.1437   0.04024   0.03088  -0.0384   0.0608   0.8198
  10.000   1.1622   0.04214   0.03313  -0.0377   0.0592   0.8226
  10.250   1.1777   0.04385   0.03511  -0.0365   0.0576   0.8250
  10.500   1.1913   0.04528   0.03673  -0.0350   0.0563   0.8274
  10.750   1.2054   0.04654   0.03809  -0.0337   0.0552   0.8303
  11.000   1.2206   0.04781   0.03937  -0.0327   0.0542   0.8335
  11.250   1.2229   0.05040   0.04238  -0.0304   0.0531   0.8368
  11.500   1.2198   0.05310   0.04547  -0.0278   0.0522   0.8401
  11.750   1.2126   0.05582   0.04852  -0.0247   0.0516   0.8428
  12.000   1.2036   0.05885   0.05186  -0.0223   0.0510   0.8457
  12.250   1.1922   0.06221   0.05553  -0.0204   0.0505   0.8487
  12.500   1.1781   0.06601   0.05961  -0.0193   0.0501   0.8517
  12.750   1.1599   0.07058   0.06445  -0.0191   0.0498   0.8547
  13.000   1.1343   0.07641   0.07059  -0.0203   0.0496   0.8571
  13.250   1.0745   0.08808   0.08272  -0.0259   0.0498   0.8582
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