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NASA SC(2)-0010 AIRFOIL (sc20010-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0010 AIRFOIL (sc20010-il)
Reynolds number: 200,000
Max Cl/Cd: 39.04 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20010-il-200000-n5.txt
Download as CSV file: xf-sc20010-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0010 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
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.9344   0.06621   0.06200  -0.0209   1.0000   0.0206
 -12.000  -0.9788   0.05680   0.05223  -0.0256   1.0000   0.0205
 -11.750  -1.0042   0.05146   0.04659  -0.0259   1.0000   0.0205
 -11.500  -1.0217   0.04761   0.04246  -0.0242   1.0000   0.0206
 -11.250  -1.0322   0.04460   0.03917  -0.0216   1.0000   0.0208
 -11.000  -1.0337   0.04180   0.03607  -0.0196   1.0000   0.0211
 -10.750  -1.0303   0.03918   0.03313  -0.0179   1.0000   0.0216
 -10.500  -1.0238   0.03657   0.03017  -0.0162   1.0000   0.0221
 -10.250  -1.0140   0.03409   0.02730  -0.0146   1.0000   0.0226
 -10.000  -1.0007   0.03186   0.02470  -0.0133   1.0000   0.0231
  -9.750  -0.9844   0.03002   0.02264  -0.0122   1.0000   0.0235
  -9.500  -0.9658   0.02868   0.02119  -0.0114   1.0000   0.0239
  -9.250  -0.9460   0.02752   0.01993  -0.0106   1.0000   0.0245
  -9.000  -0.9255   0.02638   0.01867  -0.0099   1.0000   0.0251
  -8.750  -0.9044   0.02524   0.01739  -0.0091   1.0000   0.0258
  -8.500  -0.8828   0.02410   0.01609  -0.0084   1.0000   0.0267
  -8.250  -0.8606   0.02301   0.01483  -0.0077   1.0000   0.0278
  -8.000  -0.8385   0.02210   0.01387  -0.0071   1.0000   0.0290
  -7.750  -0.8153   0.02143   0.01317  -0.0066   1.0000   0.0304
  -7.500  -0.7921   0.02068   0.01234  -0.0060   1.0000   0.0321
  -7.250  -0.7687   0.01988   0.01141  -0.0054   1.0000   0.0338
  -7.000  -0.7459   0.01911   0.01066  -0.0048   1.0000   0.0356
  -6.750  -0.7222   0.01850   0.01002  -0.0042   1.0000   0.0379
  -6.500  -0.6982   0.01792   0.00935  -0.0036   1.0000   0.0407
  -6.250  -0.6748   0.01734   0.00881  -0.0031   1.0000   0.0439
  -6.000  -0.6506   0.01688   0.00831  -0.0026   1.0000   0.0477
  -5.750  -0.6272   0.01632   0.00775  -0.0020   1.0000   0.0514
  -5.500  -0.6035   0.01591   0.00733  -0.0014   1.0000   0.0558
  -5.250  -0.5802   0.01547   0.00688  -0.0007   1.0000   0.0604
  -5.000  -0.5577   0.01504   0.00650   0.0001   1.0000   0.0655
  -4.750  -0.5354   0.01471   0.00614   0.0010   1.0000   0.0706
  -4.500  -0.5107   0.01426   0.00575   0.0013   0.9978   0.0771
  -4.250  -0.4766   0.01384   0.00534  -0.0003   0.9903   0.0857
  -4.000  -0.4426   0.01344   0.00497  -0.0019   0.9823   0.0973
  -3.750  -0.4096   0.01300   0.00463  -0.0033   0.9730   0.1155
  -3.500  -0.3775   0.01254   0.00431  -0.0046   0.9634   0.1447
  -3.250  -0.3456   0.01200   0.00400  -0.0058   0.9547   0.1957
  -3.000  -0.3168   0.01134   0.00371  -0.0065   0.9442   0.2797
  -2.750  -0.2899   0.01051   0.00342  -0.0069   0.9344   0.4036
  -2.500  -0.2658   0.00969   0.00333  -0.0063   0.9247   0.5617
  -2.250  -0.2397   0.00950   0.00343  -0.0056   0.9151   0.6562
  -2.000  -0.2115   0.00946   0.00343  -0.0054   0.9069   0.6931
  -1.750  -0.1844   0.00943   0.00342  -0.0049   0.8975   0.7204
  -1.500  -0.1579   0.00941   0.00345  -0.0042   0.8897   0.7471
  -1.250  -0.1316   0.00940   0.00349  -0.0035   0.8812   0.7705
  -1.000  -0.1056   0.00940   0.00352  -0.0026   0.8741   0.7906
  -0.750  -0.0795   0.00941   0.00357  -0.0019   0.8667   0.8084
  -0.500  -0.0531   0.00942   0.00360  -0.0012   0.8600   0.8234
  -0.250  -0.0267   0.00943   0.00363  -0.0005   0.8538   0.8361
   0.000   0.0000   0.00943   0.00366   0.0000   0.8457   0.8457
   0.250   0.0267   0.00943   0.00363   0.0005   0.8360   0.8538
   0.500   0.0531   0.00942   0.00360   0.0012   0.8233   0.8600
   0.750   0.0795   0.00941   0.00357   0.0019   0.8084   0.8667
   1.000   0.1056   0.00940   0.00352   0.0026   0.7907   0.8741
   1.250   0.1316   0.00940   0.00349   0.0035   0.7705   0.8811
   1.500   0.1579   0.00940   0.00345   0.0042   0.7471   0.8897
   1.750   0.1843   0.00943   0.00342   0.0049   0.7205   0.8975
   2.000   0.2115   0.00946   0.00343   0.0054   0.6930   0.9069
   2.250   0.2397   0.00950   0.00343   0.0056   0.6563   0.9151
   2.500   0.2658   0.00969   0.00333   0.0063   0.5624   0.9247
   2.750   0.2899   0.01050   0.00342   0.0069   0.4036   0.9344
   3.000   0.3168   0.01134   0.00371   0.0065   0.2796   0.9442
   3.250   0.3456   0.01200   0.00400   0.0058   0.1957   0.9547
   3.500   0.3775   0.01254   0.00431   0.0046   0.1446   0.9635
   3.750   0.4097   0.01300   0.00462   0.0033   0.1155   0.9731
   4.000   0.4426   0.01343   0.00497   0.0019   0.0973   0.9824
   4.250   0.4767   0.01384   0.00534   0.0003   0.0857   0.9904
   4.500   0.5108   0.01426   0.00575  -0.0013   0.0771   0.9979
   4.750   0.5353   0.01471   0.00613  -0.0010   0.0706   1.0000
   5.000   0.5577   0.01504   0.00650  -0.0001   0.0655   1.0000
   5.250   0.5802   0.01547   0.00688   0.0007   0.0604   1.0000
   5.500   0.6035   0.01591   0.00733   0.0014   0.0558   1.0000
   5.750   0.6272   0.01632   0.00775   0.0020   0.0514   1.0000
   6.000   0.6506   0.01688   0.00831   0.0026   0.0477   1.0000
   6.250   0.6748   0.01734   0.00881   0.0031   0.0439   1.0000
   6.500   0.6982   0.01793   0.00935   0.0036   0.0407   1.0000
   6.750   0.7222   0.01850   0.01002   0.0042   0.0379   1.0000
   7.000   0.7459   0.01911   0.01066   0.0048   0.0356   1.0000
   7.250   0.7687   0.01988   0.01141   0.0054   0.0338   1.0000
   7.500   0.7921   0.02068   0.01234   0.0060   0.0321   1.0000
   7.750   0.8154   0.02143   0.01317   0.0066   0.0303   1.0000
   8.000   0.8385   0.02210   0.01386   0.0071   0.0290   1.0000
   8.250   0.8607   0.02302   0.01483   0.0077   0.0278   1.0000
   8.500   0.8828   0.02410   0.01609   0.0084   0.0267   1.0000
   8.750   0.9044   0.02524   0.01739   0.0091   0.0258   1.0000
   9.000   0.9256   0.02638   0.01867   0.0099   0.0251   1.0000
   9.250   0.9461   0.02752   0.01993   0.0106   0.0245   1.0000
   9.500   0.9659   0.02868   0.02119   0.0114   0.0239   1.0000
   9.750   0.9845   0.03002   0.02264   0.0122   0.0235   1.0000
  10.000   1.0008   0.03187   0.02471   0.0133   0.0231   1.0000
  10.250   1.0141   0.03409   0.02730   0.0146   0.0226   1.0000
  10.500   1.0240   0.03658   0.03018   0.0162   0.0221   1.0000
  10.750   1.0305   0.03918   0.03313   0.0178   0.0216   1.0000
  11.000   1.0339   0.04180   0.03607   0.0196   0.0211   1.0000
  11.250   1.0324   0.04462   0.03919   0.0215   0.0208   1.0000
  11.500   1.0221   0.04762   0.04247   0.0241   0.0206   1.0000
  11.750   1.0046   0.05150   0.04663   0.0258   0.0205   1.0000
  12.000   0.9793   0.05684   0.05227   0.0254   0.0205   1.0000
  12.250   0.9344   0.06636   0.06216   0.0206   0.0206   1.0000
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