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NASA SC(2)-1006 AIRFOIL (sc21006-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-1006 AIRFOIL (sc21006-il)
Reynolds number: 1,000,000
Max Cl/Cd: 100.17 at α=-3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc21006-il-1000000-n5.txt
Download as CSV file: xf-sc21006-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-1006 AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.5357   0.10534   0.10365  -0.0204   0.9999   0.0040
 -12.500  -0.5396   0.10137   0.09970  -0.0208   0.9999   0.0040
 -12.250  -0.5414   0.09731   0.09565  -0.0219   0.9997   0.0041
 -12.000  -0.5378   0.09197   0.09033  -0.0258   0.9988   0.0042
 -11.750  -0.5340   0.08636   0.08473  -0.0302   0.9975   0.0043
 -11.250  -0.5408   0.02423   0.02140  -0.1059   0.9853   0.0050
 -11.000  -0.5071   0.01991   0.01654  -0.1111   0.9850   0.0053
 -10.750  -0.4741   0.01756   0.01383  -0.1143   0.9848   0.0055
 -10.500  -0.4416   0.01608   0.01212  -0.1165   0.9846   0.0057
 -10.250  -0.4099   0.01532   0.01120  -0.1182   0.9843   0.0059
 -10.000  -0.3767   0.01386   0.00950  -0.1204   0.9841   0.0062
  -9.750  -0.3423   0.01212   0.00750  -0.1230   0.9840   0.0068
  -9.500  -0.3102   0.01155   0.00685  -0.1245   0.9837   0.0072
  -9.250  -0.2783   0.01105   0.00628  -0.1259   0.9834   0.0076
  -9.000  -0.2466   0.01054   0.00567  -0.1272   0.9830   0.0080
  -8.750  -0.2169   0.01006   0.00512  -0.1280   0.9819   0.0083
  -8.500  -0.1861   0.00959   0.00457  -0.1290   0.9809   0.0086
  -8.250  -0.1550   0.00916   0.00407  -0.1301   0.9800   0.0089
  -8.000  -0.1240   0.00882   0.00368  -0.1311   0.9792   0.0094
  -7.750  -0.0930   0.00854   0.00334  -0.1321   0.9783   0.0098
  -7.500  -0.0617   0.00825   0.00299  -0.1331   0.9776   0.0100
  -7.250  -0.0293   0.00785   0.00252  -0.1343   0.9769   0.0122
  -7.000   0.0019   0.00763   0.00231  -0.1353   0.9761   0.0150
  -6.750   0.0329   0.00747   0.00213  -0.1361   0.9752   0.0172
  -6.500   0.0643   0.00728   0.00195  -0.1371   0.9743   0.0230
  -6.250   0.0953   0.00711   0.00180  -0.1379   0.9736   0.0307
  -6.000   0.1266   0.00691   0.00168  -0.1389   0.9729   0.0500
  -5.750   0.1585   0.00662   0.00156  -0.1401   0.9724   0.0955
  -5.500   0.1899   0.00643   0.00146  -0.1412   0.9718   0.1308
  -5.250   0.2215   0.00622   0.00138  -0.1422   0.9712   0.1711
  -5.000   0.2538   0.00593   0.00132  -0.1436   0.9707   0.2444
  -4.750   0.2860   0.00564   0.00130  -0.1449   0.9700   0.3297
  -4.500   0.3146   0.00549   0.00128  -0.1451   0.9669   0.3773
  -4.250   0.3439   0.00537   0.00123  -0.1455   0.9626   0.4016
  -4.000   0.3744   0.00522   0.00116  -0.1460   0.9583   0.4300
  -3.750   0.4034   0.00509   0.00115  -0.1462   0.9529   0.4708
  -3.500   0.4320   0.00498   0.00110  -0.1462   0.9439   0.4992
  -3.250   0.4596   0.00489   0.00106  -0.1459   0.9297   0.5286
  -3.000   0.4858   0.00485   0.00100  -0.1453   0.8974   0.5533
  -2.750   0.5022   0.00584   0.00109  -0.1423   0.6798   0.5686
  -2.500   0.5224   0.00701   0.00143  -0.1410   0.4633   0.5867
  -2.250   0.5470   0.00768   0.00164  -0.1406   0.3307   0.6068
  -2.000   0.5727   0.00818   0.00184  -0.1403   0.2332   0.6282
  -1.750   0.5983   0.00873   0.00207  -0.1401   0.1308   0.6504
  -1.500   0.6243   0.00920   0.00229  -0.1398   0.0571   0.6703
  -1.250   0.6515   0.00943   0.00248  -0.1396   0.0355   0.6850
  -1.000   0.6788   0.00964   0.00266  -0.1395   0.0250   0.6969
  -0.750   0.7061   0.00984   0.00287  -0.1393   0.0189   0.7075
  -0.500   0.7334   0.01000   0.00306  -0.1391   0.0165   0.7178
  -0.250   0.7604   0.01025   0.00330  -0.1389   0.0124   0.7286
   0.000   0.7873   0.01050   0.00362  -0.1386   0.0110   0.7384
   0.250   0.8142   0.01074   0.00391  -0.1383   0.0102   0.7479
   0.500   0.8409   0.01101   0.00423  -0.1380   0.0095   0.7576
   0.750   0.8674   0.01130   0.00456  -0.1376   0.0088   0.7666
   1.000   0.8938   0.01162   0.00492  -0.1372   0.0081   0.7739
   1.250   0.9195   0.01210   0.00548  -0.1366   0.0074   0.7817
   1.500   0.9433   0.01301   0.00654  -0.1356   0.0067   0.7895
   1.750   0.9685   0.01357   0.00718  -0.1349   0.0066   0.7983
   2.000   0.9934   0.01421   0.00793  -0.1342   0.0066   0.8075
   2.250   1.0186   0.01474   0.00855  -0.1336   0.0064   0.8155
   2.500   1.0437   0.01533   0.00922  -0.1329   0.0061   0.8223
   2.750   1.0680   0.01615   0.01019  -0.1321   0.0060   0.8279
   3.000   1.0922   0.01708   0.01125  -0.1312   0.0058   0.8339
   3.250   1.1163   0.01806   0.01239  -0.1303   0.0056   0.8393
   3.500   1.1399   0.01916   0.01366  -0.1293   0.0054   0.8451
   4.000   1.1868   0.02126   0.01608  -0.1274   0.0049   0.8570
   4.250   1.2105   0.02192   0.01686  -0.1267   0.0047   0.8642
   4.500   1.2343   0.02231   0.01733  -0.1260   0.0045   0.8727
   4.750   1.2582   0.02260   0.01771  -0.1253   0.0043   0.8821
   5.250   1.2924   0.02726   0.02307  -0.1214   0.0038   0.9040
   5.750   1.3127   0.03397   0.03070  -0.1150   0.0036   1.0001
   7.250   1.0765   0.11005   0.10896  -0.1066   0.0032   1.0001
   7.500   1.0630   0.11876   0.11765  -0.1124   0.0032   1.0001
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