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NASA SC(2)-0610 AIRFOIL (sc20610-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NASA SC(2)-0610 AIRFOIL (sc20610-il)
Reynolds number: 500,000
Max Cl/Cd: 64.91 at α=0.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc20610-il-500000.txt
Download as CSV file: xf-sc20610-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0610 AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.7071   0.09426   0.09166  -0.0313   1.0000   0.0239
 -12.750  -0.8095   0.06383   0.06092  -0.0530   1.0000   0.0223
 -12.500  -0.8484   0.05514   0.05200  -0.0584   1.0000   0.0220
 -12.250  -0.8824   0.04889   0.04551  -0.0600   1.0000   0.0218
 -12.000  -0.9133   0.04464   0.04106  -0.0583   1.0000   0.0217
 -11.750  -0.9381   0.04079   0.03696  -0.0563   1.0000   0.0216
 -11.500  -0.9485   0.03680   0.03264  -0.0557   1.0000   0.0216
 -11.250  -0.9480   0.03354   0.02905  -0.0548   1.0000   0.0217
 -11.000  -0.9400   0.03088   0.02609  -0.0541   1.0000   0.0219
 -10.750  -0.9271   0.02863   0.02357  -0.0536   1.0000   0.0222
 -10.500  -0.9110   0.02673   0.02143  -0.0531   1.0000   0.0225
 -10.250  -0.8924   0.02515   0.01965  -0.0527   1.0000   0.0228
 -10.000  -0.8721   0.02393   0.01824  -0.0524   1.0000   0.0232
  -9.750  -0.8515   0.02245   0.01656  -0.0521   1.0000   0.0237
  -9.500  -0.8306   0.02090   0.01494  -0.0519   1.0000   0.0244
  -9.250  -0.8078   0.02005   0.01405  -0.0517   1.0000   0.0250
  -9.000  -0.7844   0.01929   0.01324  -0.0515   1.0000   0.0256
  -8.750  -0.7604   0.01854   0.01242  -0.0514   1.0000   0.0263
  -8.500  -0.7357   0.01783   0.01163  -0.0514   1.0000   0.0271
  -8.250  -0.7106   0.01719   0.01092  -0.0514   1.0000   0.0280
  -8.000  -0.6846   0.01643   0.01007  -0.0516   1.0000   0.0289
  -7.750  -0.6575   0.01557   0.00922  -0.0523   1.0000   0.0305
  -7.500  -0.6308   0.01516   0.00881  -0.0526   1.0000   0.0322
  -7.250  -0.6038   0.01484   0.00845  -0.0529   1.0000   0.0341
  -7.000  -0.5738   0.01415   0.00775  -0.0540   1.0000   0.0370
  -6.750  -0.5457   0.01386   0.00747  -0.0545   1.0000   0.0399
  -6.500  -0.5159   0.01342   0.00700  -0.0554   1.0000   0.0434
  -6.250  -0.4866   0.01310   0.00671  -0.0562   1.0000   0.0473
  -6.000  -0.4588   0.01295   0.00653  -0.0566   1.0000   0.0506
  -5.750  -0.4242   0.01248   0.00611  -0.0585   0.9995   0.0567
  -5.500  -0.3897   0.01233   0.00592  -0.0602   0.9984   0.0612
  -5.250  -0.3535   0.01191   0.00556  -0.0625   0.9977   0.0697
  -5.000  -0.3176   0.01161   0.00531  -0.0646   0.9968   0.0793
  -4.750  -0.2814   0.01133   0.00508  -0.0667   0.9959   0.0925
  -4.500  -0.2443   0.01098   0.00486  -0.0691   0.9952   0.1177
  -4.250  -0.2054   0.01040   0.00464  -0.0723   0.9951   0.1943
  -4.000  -0.1631   0.00945   0.00436  -0.0767   0.9958   0.3536
  -3.750  -0.1203   0.00860   0.00429  -0.0809   0.9970   0.5501
  -3.500  -0.0850   0.00860   0.00442  -0.0825   0.9958   0.6099
  -3.250  -0.0496   0.00867   0.00452  -0.0841   0.9946   0.6341
  -3.000  -0.0158   0.00875   0.00461  -0.0853   0.9927   0.6506
  -2.750   0.0169   0.00882   0.00469  -0.0863   0.9902   0.6630
  -2.500   0.0515   0.00891   0.00474  -0.0877   0.9880   0.6737
  -2.250   0.0877   0.00896   0.00485  -0.0893   0.9857   0.6820
  -2.000   0.1277   0.00904   0.00496  -0.0915   0.9835   0.6941
  -1.750   0.1628   0.00895   0.00490  -0.0926   0.9765   0.7021
  -1.500   0.2062   0.00879   0.00476  -0.0956   0.9731   0.7083
  -1.250   0.2451   0.00866   0.00468  -0.0974   0.9685   0.7132
  -1.000   0.2885   0.00839   0.00443  -0.1002   0.9622   0.7192
  -0.750   0.3288   0.00806   0.00412  -0.1022   0.9533   0.7234
  -0.500   0.3629   0.00787   0.00397  -0.1029   0.9437   0.7262
  -0.250   0.3912   0.00782   0.00395  -0.1025   0.9310   0.7291
   0.000   0.4205   0.00776   0.00390  -0.1024   0.9157   0.7322
   0.250   0.4495   0.00772   0.00384  -0.1022   0.8954   0.7354
   0.500   0.4785   0.00771   0.00375  -0.1020   0.8668   0.7381
   0.750   0.5050   0.00778   0.00366  -0.1012   0.8111   0.7399
   1.000   0.5238   0.00853   0.00369  -0.0987   0.6434   0.7415
   1.250   0.5409   0.00984   0.00405  -0.0967   0.4337   0.7433
   1.500   0.5627   0.01083   0.00438  -0.0958   0.2810   0.7452
   1.750   0.5867   0.01162   0.00467  -0.0953   0.1726   0.7474
   2.000   0.6126   0.01218   0.00494  -0.0950   0.1162   0.7498
   2.250   0.6401   0.01255   0.00519  -0.0950   0.0927   0.7523
   2.500   0.6681   0.01289   0.00545  -0.0951   0.0795   0.7548
   2.750   0.6949   0.01324   0.00575  -0.0949   0.0696   0.7566
   3.000   0.7219   0.01347   0.00599  -0.0946   0.0638   0.7582
   3.250   0.7479   0.01390   0.00642  -0.0942   0.0578   0.7599
   3.500   0.7751   0.01414   0.00668  -0.0940   0.0535   0.7619
   3.750   0.8007   0.01468   0.00718  -0.0935   0.0482   0.7642
   4.000   0.8283   0.01490   0.00744  -0.0934   0.0450   0.7669
   4.250   0.8553   0.01530   0.00781  -0.0932   0.0413   0.7696
   4.500   0.8817   0.01582   0.00835  -0.0930   0.0382   0.7718
   4.750   0.9077   0.01616   0.00872  -0.0925   0.0355   0.7734
   5.000   0.9309   0.01702   0.00959  -0.0916   0.0329   0.7752
   5.250   0.9571   0.01738   0.01002  -0.0912   0.0314   0.7771
   5.500   0.9829   0.01780   0.01048  -0.0907   0.0297   0.7793
   5.750   1.0084   0.01832   0.01100  -0.0903   0.0284   0.7817
   6.000   1.0309   0.01960   0.01231  -0.0894   0.0270   0.7842
   6.250   1.0570   0.02020   0.01300  -0.0890   0.0264   0.7870
   6.500   1.0812   0.02092   0.01383  -0.0882   0.0257   0.7890
   6.750   1.1050   0.02173   0.01475  -0.0874   0.0250   0.7909
   7.000   1.1288   0.02258   0.01570  -0.0866   0.0244   0.7931
   7.250   1.1525   0.02343   0.01664  -0.0859   0.0238   0.7956
   7.500   1.1760   0.02438   0.01766  -0.0852   0.0233   0.7982
   7.750   1.1988   0.02555   0.01890  -0.0845   0.0228   0.8009
   8.000   1.2174   0.02816   0.02172  -0.0832   0.0221   0.8031
   8.250   1.2384   0.02908   0.02286  -0.0820   0.0218   0.8051
   8.500   1.2572   0.03064   0.02468  -0.0805   0.0215   0.8073
   8.750   1.2737   0.03260   0.02694  -0.0788   0.0212   0.8097
   9.000   1.2872   0.03501   0.02969  -0.0767   0.0210   0.8123
   9.250   1.2962   0.03800   0.03306  -0.0742   0.0208   0.8149
   9.500   1.2981   0.04186   0.03735  -0.0710   0.0206   0.8173
   9.750   1.2869   0.04699   0.04300  -0.0664   0.0207   0.8193
  10.000   1.2608   0.05320   0.04973  -0.0609   0.0208   0.8212
  10.250   1.2266   0.05833   0.05522  -0.0547   0.0211   0.8235
  10.500   1.1914   0.06361   0.06077  -0.0504   0.0212   0.8260
  10.750   1.1566   0.06970   0.06710  -0.0490   0.0214   0.8283
  11.000   1.1235   0.07695   0.07453  -0.0511   0.0216   0.8305
  11.250   1.0867   0.08794   0.08571  -0.0592   0.0218   0.8322
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