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NASA SC(2)-0412 AIRFOIL (sc20412-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0412 AIRFOIL (sc20412-il)
Reynolds number: 100,000
Max Cl/Cd: 30.43 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20412-il-100000-n5.txt
Download as CSV file: xf-sc20412-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0412 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
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.8122   0.07759   0.07127  -0.0422   1.0000   0.0431
 -12.250  -0.8536   0.06854   0.06195  -0.0474   1.0000   0.0428
 -12.000  -0.8818   0.06248   0.05563  -0.0496   1.0000   0.0429
 -11.750  -0.9031   0.05780   0.05070  -0.0503   1.0000   0.0432
 -11.500  -0.9205   0.05394   0.04657  -0.0500   1.0000   0.0436
 -11.250  -0.9350   0.05060   0.04294  -0.0488   1.0000   0.0441
 -11.000  -0.9417   0.04718   0.03913  -0.0482   1.0000   0.0448
 -10.750  -0.9428   0.04395   0.03543  -0.0473   1.0000   0.0456
 -10.500  -0.9306   0.04206   0.03347  -0.0466   1.0000   0.0463
 -10.250  -0.9166   0.04056   0.03190  -0.0459   1.0000   0.0474
 -10.000  -0.9025   0.03907   0.03028  -0.0452   1.0000   0.0488
  -9.750  -0.8882   0.03737   0.02836  -0.0444   1.0000   0.0505
  -9.500  -0.8733   0.03548   0.02611  -0.0436   1.0000   0.0524
  -9.250  -0.8555   0.03395   0.02448  -0.0427   1.0000   0.0538
  -9.000  -0.8368   0.03278   0.02330  -0.0420   1.0000   0.0553
  -8.750  -0.8179   0.03167   0.02209  -0.0412   1.0000   0.0575
  -8.500  -0.7984   0.03046   0.02068  -0.0404   1.0000   0.0601
  -8.250  -0.7785   0.02925   0.01938  -0.0395   1.0000   0.0622
  -8.000  -0.7586   0.02829   0.01846  -0.0387   1.0000   0.0642
  -7.750  -0.7382   0.02741   0.01755  -0.0378   1.0000   0.0671
  -7.500  -0.7174   0.02654   0.01653  -0.0369   1.0000   0.0703
  -7.250  -0.6973   0.02561   0.01565  -0.0360   1.0000   0.0729
  -7.000  -0.6767   0.02484   0.01491  -0.0352   1.0000   0.0762
  -6.750  -0.6556   0.02414   0.01414  -0.0344   1.0000   0.0803
  -6.500  -0.6349   0.02334   0.01337  -0.0336   1.0000   0.0841
  -6.250  -0.6136   0.02265   0.01272  -0.0329   1.0000   0.0886
  -6.000  -0.5916   0.02207   0.01206  -0.0322   1.0000   0.0942
  -5.750  -0.5698   0.02132   0.01143  -0.0318   1.0000   0.1001
  -5.500  -0.5469   0.02076   0.01084  -0.0314   1.0000   0.1076
  -5.250  -0.5236   0.02010   0.01030  -0.0313   1.0000   0.1168
  -5.000  -0.4995   0.01952   0.00980  -0.0313   1.0000   0.1288
  -4.750  -0.4747   0.01894   0.00933  -0.0314   1.0000   0.1468
  -4.500  -0.4488   0.01833   0.00891  -0.0319   1.0000   0.1750
  -4.250  -0.4212   0.01756   0.00847  -0.0329   1.0000   0.2275
  -4.000  -0.3889   0.01637   0.00796  -0.0355   1.0000   0.3426
  -3.750  -0.3666   0.01595   0.00856  -0.0345   1.0000   0.5030
  -3.500  -0.3486   0.01646   0.00929  -0.0317   1.0000   0.5734
  -3.250  -0.3225   0.01673   0.00950  -0.0315   1.0000   0.6115
  -3.000  -0.2994   0.01714   0.00987  -0.0304   1.0000   0.6360
  -2.750  -0.2653   0.01751   0.01014  -0.0316   0.9962   0.6585
  -2.500  -0.2345   0.01802   0.01063  -0.0316   0.9914   0.6735
  -2.250  -0.2064   0.01862   0.01122  -0.0308   0.9861   0.6885
  -2.000  -0.1783   0.01929   0.01190  -0.0298   0.9812   0.7037
  -1.750  -0.1510   0.01974   0.01235  -0.0290   0.9751   0.7174
  -1.500  -0.1181   0.02004   0.01261  -0.0296   0.9707   0.7280
  -1.250  -0.0883   0.02014   0.01270  -0.0299   0.9645   0.7345
  -1.000  -0.0562   0.02021   0.01276  -0.0306   0.9592   0.7392
  -0.750  -0.0181   0.02018   0.01270  -0.0330   0.9558   0.7443
  -0.500   0.0154   0.02007   0.01258  -0.0348   0.9490   0.7495
  -0.250   0.0490   0.02005   0.01258  -0.0358   0.9439   0.7521
   0.000   0.0826   0.02002   0.01258  -0.0370   0.9385   0.7552
   0.250   0.1182   0.01990   0.01249  -0.0386   0.9304   0.7584
   0.500   0.1618   0.01963   0.01225  -0.0417   0.9217   0.7616
   0.750   0.2065   0.01926   0.01189  -0.0449   0.9108   0.7647
   1.000   0.2462   0.01881   0.01149  -0.0464   0.8943   0.7670
   1.250   0.2806   0.01836   0.01108  -0.0466   0.8721   0.7689
   1.500   0.3124   0.01802   0.01078  -0.0465   0.8490   0.7709
   1.750   0.3451   0.01772   0.01051  -0.0468   0.8259   0.7731
   2.000   0.3759   0.01748   0.01028  -0.0468   0.7957   0.7754
   2.250   0.4077   0.01726   0.01001  -0.0469   0.7541   0.7781
   2.500   0.4394   0.01716   0.00977  -0.0470   0.6917   0.7813
   2.750   0.4656   0.01736   0.00947  -0.0458   0.5675   0.7836
   3.000   0.4834   0.01829   0.00955  -0.0436   0.4068   0.7857
   3.250   0.5036   0.01919   0.00987  -0.0424   0.2961   0.7881
   3.500   0.5267   0.01993   0.01021  -0.0419   0.2234   0.7908
   3.750   0.5522   0.02054   0.01058  -0.0419   0.1811   0.7935
   4.000   0.5790   0.02112   0.01100  -0.0421   0.1562   0.7960
   4.250   0.6071   0.02167   0.01146  -0.0426   0.1384   0.7986
   4.500   0.6315   0.02221   0.01194  -0.0421   0.1263   0.8005
   4.750   0.6557   0.02272   0.01246  -0.0415   0.1163   0.8026
   5.000   0.6802   0.02328   0.01303  -0.0410   0.1081   0.8051
   5.250   0.7053   0.02389   0.01360  -0.0408   0.1013   0.8079
   5.500   0.7316   0.02454   0.01430  -0.0407   0.0950   0.8109
   5.750   0.7589   0.02519   0.01495  -0.0410   0.0892   0.8138
   6.000   0.7850   0.02596   0.01572  -0.0410   0.0845   0.8162
   6.250   0.8091   0.02661   0.01646  -0.0404   0.0798   0.8184
   6.500   0.8328   0.02737   0.01719  -0.0399   0.0761   0.8211
   6.750   0.8582   0.02823   0.01819  -0.0396   0.0722   0.8241
   7.000   0.8841   0.02911   0.01915  -0.0395   0.0686   0.8271
   7.250   0.9102   0.03007   0.02007  -0.0398   0.0658   0.8300
   7.500   0.9356   0.03118   0.02139  -0.0396   0.0626   0.8324
   7.750   0.9586   0.03219   0.02256  -0.0389   0.0597   0.8349
   8.000   0.9816   0.03322   0.02364  -0.0384   0.0576   0.8379
   8.250   1.0048   0.03456   0.02508  -0.0381   0.0556   0.8412
   8.500   1.0276   0.03608   0.02694  -0.0377   0.0530   0.8447
   8.750   1.0495   0.03738   0.02841  -0.0373   0.0510   0.8477
   9.000   1.0691   0.03865   0.02979  -0.0364   0.0497   0.8505
   9.250   1.0881   0.04032   0.03159  -0.0356   0.0485   0.8535
   9.500   1.1019   0.04285   0.03466  -0.0341   0.0468   0.8567
   9.750   1.1156   0.04509   0.03725  -0.0330   0.0452   0.8601
  10.000   1.1289   0.04690   0.03930  -0.0318   0.0439   0.8635
  10.250   1.1411   0.04844   0.04098  -0.0304   0.0430   0.8671
  10.500   1.1529   0.05019   0.04283  -0.0291   0.0423   0.8711
  10.750   1.1510   0.05367   0.04675  -0.0269   0.0417   0.8753
  11.000   1.1369   0.05782   0.05143  -0.0238   0.0413   0.8792
  11.250   1.1146   0.06174   0.05575  -0.0203   0.0410   0.8835
  11.500   1.0890   0.06660   0.06098  -0.0185   0.0409   0.8880
  11.750   1.0585   0.07270   0.06742  -0.0190   0.0408   0.8919
  12.000   1.0211   0.08059   0.07563  -0.0221   0.0410   0.8952
  12.250   0.9740   0.09281   0.08812  -0.0307   0.0414   0.8979
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