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NASA SC(2)-0012 AIRFOIL (sc20012-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0012 AIRFOIL (sc20012-il)
Reynolds number: 200,000
Max Cl/Cd: 39.88 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20012-il-200000-n5.txt
Download as CSV file: xf-sc20012-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0012 AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.750  -0.9984   0.08336   0.07878  -0.0187   1.0000   0.0246
 -14.500  -1.0455   0.07076   0.06582  -0.0271   1.0000   0.0244
 -14.250  -1.0719   0.06348   0.05828  -0.0308   1.0000   0.0245
 -14.000  -1.0906   0.05803   0.05259  -0.0326   1.0000   0.0246
 -13.750  -1.1045   0.05359   0.04791  -0.0335   1.0000   0.0248
 -13.500  -1.1150   0.04980   0.04386  -0.0335   1.0000   0.0251
 -13.250  -1.1227   0.04648   0.04028  -0.0330   1.0000   0.0254
 -13.000  -1.1277   0.04354   0.03708  -0.0319   1.0000   0.0258
 -12.750  -1.1299   0.04093   0.03419  -0.0305   1.0000   0.0261
 -12.500  -1.1280   0.03878   0.03183  -0.0290   1.0000   0.0265
 -12.250  -1.1216   0.03725   0.03023  -0.0274   1.0000   0.0268
 -12.000  -1.1142   0.03589   0.02879  -0.0257   1.0000   0.0271
 -11.750  -1.1059   0.03463   0.02742  -0.0239   1.0000   0.0276
 -11.500  -1.0967   0.03341   0.02609  -0.0219   1.0000   0.0281
 -11.250  -1.0846   0.03216   0.02471  -0.0203   1.0000   0.0287
 -11.000  -1.0707   0.03086   0.02325  -0.0189   1.0000   0.0295
 -10.750  -1.0554   0.02956   0.02174  -0.0176   1.0000   0.0304
 -10.500  -1.0391   0.02845   0.02054  -0.0164   1.0000   0.0312
 -10.250  -1.0215   0.02763   0.01969  -0.0153   1.0000   0.0320
 -10.000  -1.0027   0.02683   0.01882  -0.0144   1.0000   0.0332
  -9.750  -0.9832   0.02595   0.01782  -0.0134   1.0000   0.0348
  -9.500  -0.9636   0.02506   0.01682  -0.0125   1.0000   0.0362
  -9.250  -0.9433   0.02437   0.01612  -0.0117   1.0000   0.0375
  -9.000  -0.9224   0.02366   0.01535  -0.0108   1.0000   0.0392
  -8.750  -0.9009   0.02291   0.01446  -0.0100   1.0000   0.0410
  -8.500  -0.8801   0.02219   0.01374  -0.0092   1.0000   0.0426
  -8.250  -0.8582   0.02162   0.01316  -0.0085   1.0000   0.0446
  -8.000  -0.8358   0.02106   0.01250  -0.0078   1.0000   0.0471
  -7.750  -0.8143   0.02042   0.01186  -0.0070   1.0000   0.0492
  -7.500  -0.7921   0.01992   0.01136  -0.0062   1.0000   0.0517
  -7.250  -0.7697   0.01944   0.01081  -0.0054   1.0000   0.0545
  -7.000  -0.7489   0.01884   0.01023  -0.0045   1.0000   0.0570
  -6.750  -0.7278   0.01838   0.00979  -0.0035   1.0000   0.0598
  -6.500  -0.7075   0.01797   0.00934  -0.0023   1.0000   0.0627
  -6.250  -0.6807   0.01740   0.00879  -0.0026   0.9948   0.0659
  -6.000  -0.6481   0.01689   0.00829  -0.0040   0.9855   0.0698
  -5.750  -0.6157   0.01642   0.00779  -0.0053   0.9756   0.0740
  -5.500  -0.5841   0.01590   0.00730  -0.0065   0.9657   0.0788
  -5.250  -0.5522   0.01551   0.00686  -0.0075   0.9552   0.0843
  -5.000  -0.5226   0.01504   0.00646  -0.0082   0.9437   0.0913
  -4.750  -0.4930   0.01465   0.00607  -0.0087   0.9331   0.0999
  -4.500  -0.4648   0.01428   0.00573  -0.0090   0.9222   0.1118
  -4.250  -0.4379   0.01389   0.00541  -0.0089   0.9121   0.1281
  -4.000  -0.4114   0.01350   0.00510  -0.0088   0.9030   0.1514
  -3.750  -0.3861   0.01306   0.00482  -0.0085   0.8942   0.1843
  -3.500  -0.3615   0.01257   0.00454  -0.0081   0.8861   0.2348
  -3.250  -0.3378   0.01200   0.00426  -0.0076   0.8791   0.3036
  -3.000  -0.3156   0.01129   0.00399  -0.0069   0.8719   0.4017
  -2.750  -0.2950   0.01057   0.00385  -0.0055   0.8656   0.5253
  -2.500  -0.2717   0.01034   0.00403  -0.0043   0.8595   0.6275
  -2.250  -0.2448   0.01034   0.00406  -0.0038   0.8533   0.6668
  -2.000  -0.2177   0.01037   0.00407  -0.0034   0.8482   0.6936
  -1.750  -0.1908   0.01039   0.00410  -0.0029   0.8439   0.7151
  -1.500  -0.1634   0.01041   0.00415  -0.0025   0.8384   0.7335
  -1.250  -0.1361   0.01044   0.00419  -0.0022   0.8333   0.7497
  -1.000  -0.1091   0.01047   0.00425  -0.0016   0.8290   0.7637
  -0.750  -0.0819   0.01050   0.00430  -0.0011   0.8252   0.7764
  -0.500  -0.0543   0.01054   0.00435  -0.0009   0.8202   0.7890
  -0.250  -0.0272   0.01056   0.00443  -0.0004   0.8150   0.7998
   0.000   0.0000   0.01057   0.00443   0.0000   0.8091   0.8091
   0.250   0.0272   0.01056   0.00443   0.0004   0.7998   0.8150
   0.500   0.0543   0.01054   0.00435   0.0009   0.7890   0.8202
   0.750   0.0819   0.01050   0.00430   0.0011   0.7762   0.8252
   1.000   0.1091   0.01047   0.00425   0.0016   0.7637   0.8290
   1.250   0.1361   0.01044   0.00419   0.0022   0.7497   0.8333
   1.500   0.1634   0.01041   0.00415   0.0025   0.7335   0.8384
   1.750   0.1908   0.01039   0.00410   0.0029   0.7151   0.8439
   2.000   0.2177   0.01037   0.00407   0.0034   0.6935   0.8482
   2.250   0.2448   0.01034   0.00406   0.0038   0.6667   0.8533
   2.500   0.2717   0.01034   0.00402   0.0043   0.6274   0.8595
   2.750   0.2950   0.01057   0.00385   0.0055   0.5252   0.8656
   3.000   0.3156   0.01129   0.00399   0.0069   0.4017   0.8719
   3.250   0.3378   0.01200   0.00426   0.0076   0.3036   0.8791
   3.500   0.3615   0.01257   0.00454   0.0081   0.2349   0.8861
   3.750   0.3861   0.01306   0.00482   0.0085   0.1843   0.8942
   4.000   0.4114   0.01350   0.00510   0.0088   0.1513   0.9030
   4.250   0.4379   0.01389   0.00541   0.0089   0.1281   0.9121
   4.500   0.4648   0.01428   0.00573   0.0089   0.1118   0.9222
   4.750   0.4931   0.01465   0.00607   0.0087   0.0999   0.9331
   5.000   0.5227   0.01504   0.00646   0.0082   0.0913   0.9437
   5.250   0.5523   0.01551   0.00686   0.0075   0.0843   0.9553
   5.500   0.5841   0.01590   0.00730   0.0065   0.0788   0.9657
   5.750   0.6158   0.01642   0.00779   0.0053   0.0739   0.9757
   6.000   0.6481   0.01689   0.00828   0.0040   0.0698   0.9855
   6.250   0.6808   0.01740   0.00879   0.0026   0.0659   0.9949
   6.500   0.7074   0.01797   0.00933   0.0023   0.0627   1.0000
   6.750   0.7278   0.01838   0.00979   0.0035   0.0598   1.0000
   7.000   0.7489   0.01884   0.01023   0.0045   0.0570   1.0000
   7.250   0.7697   0.01944   0.01080   0.0054   0.0545   1.0000
   7.500   0.7921   0.01992   0.01136   0.0062   0.0517   1.0000
   7.750   0.8143   0.02042   0.01186   0.0069   0.0492   1.0000
   8.000   0.8358   0.02106   0.01250   0.0077   0.0471   1.0000
   8.250   0.8582   0.02162   0.01316   0.0085   0.0446   1.0000
   8.500   0.8802   0.02219   0.01374   0.0092   0.0426   1.0000
   8.750   0.9011   0.02291   0.01446   0.0100   0.0410   1.0000
   9.000   0.9225   0.02366   0.01535   0.0108   0.0392   1.0000
   9.250   0.9435   0.02437   0.01612   0.0116   0.0375   1.0000
   9.500   0.9637   0.02506   0.01682   0.0124   0.0362   1.0000
   9.750   0.9834   0.02595   0.01782   0.0134   0.0347   1.0000
  10.000   1.0029   0.02683   0.01882   0.0143   0.0332   1.0000
  10.250   1.0217   0.02763   0.01969   0.0153   0.0320   1.0000
  10.500   1.0394   0.02845   0.02054   0.0163   0.0312   1.0000
  10.750   1.0557   0.02956   0.02175   0.0175   0.0304   1.0000
  11.000   1.0711   0.03087   0.02325   0.0188   0.0295   1.0000
  11.250   1.0850   0.03216   0.02471   0.0203   0.0287   1.0000
  11.500   1.0971   0.03341   0.02609   0.0218   0.0281   1.0000
  11.750   1.1064   0.03463   0.02743   0.0238   0.0276   1.0000
  12.000   1.1147   0.03589   0.02879   0.0256   0.0271   1.0000
  12.250   1.1223   0.03725   0.03023   0.0273   0.0268   1.0000
  12.500   1.1287   0.03879   0.03183   0.0288   0.0265   1.0000
  12.750   1.1305   0.04095   0.03421   0.0304   0.0261   1.0000
  13.000   1.1284   0.04356   0.03710   0.0318   0.0258   1.0000
  13.250   1.1235   0.04649   0.04030   0.0328   0.0254   1.0000
  13.500   1.1159   0.04981   0.04387   0.0334   0.0251   1.0000
  13.750   1.1053   0.05361   0.04793   0.0333   0.0248   1.0000
  14.000   1.0914   0.05807   0.05263   0.0325   0.0246   1.0000
  14.250   1.0729   0.06351   0.05831   0.0306   0.0245   1.0000
  14.500   1.0465   0.07081   0.06589   0.0268   0.0244   1.0000
  14.750   0.9985   0.08363   0.07907   0.0182   0.0246   1.0000
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