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S6061 9% (s6061-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: S6061 9% (s6061-il)
Reynolds number: 500,000
Max Cl/Cd: 77.29 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s6061-il-500000-n5.txt
Download as CSV file: xf-s6061-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S6061 9%                                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5251   0.08293   0.08075  -0.0181   1.0000   0.0054
  -9.000  -0.5302   0.07725   0.07510  -0.0214   1.0000   0.0057
  -8.750  -0.5405   0.07130   0.06920  -0.0257   1.0000   0.0052
  -8.500  -0.5539   0.06426   0.06220  -0.0326   1.0000   0.0056
  -8.250  -0.5696   0.05605   0.05389  -0.0386   1.0000   0.0050
  -8.000  -0.5774   0.04830   0.04594  -0.0415   1.0000   0.0050
  -7.750  -0.5838   0.04033   0.03765  -0.0423   1.0000   0.0050
  -7.500  -0.5810   0.03418   0.03111  -0.0420   0.9976   0.0053
  -7.250  -0.5613   0.02828   0.02463  -0.0440   0.9827   0.0054
  -7.000  -0.5379   0.02427   0.02009  -0.0451   0.9715   0.0054
  -6.750  -0.5141   0.02122   0.01656  -0.0454   0.9605   0.0054
  -6.500  -0.4899   0.01905   0.01402  -0.0453   0.9499   0.0054
  -6.250  -0.4660   0.01738   0.01202  -0.0447   0.9398   0.0055
  -6.000  -0.4425   0.01606   0.01045  -0.0440   0.9297   0.0056
  -5.750  -0.4188   0.01497   0.00916  -0.0432   0.9194   0.0057
  -5.500  -0.3948   0.01404   0.00806  -0.0424   0.9099   0.0058
  -5.250  -0.3705   0.01329   0.00716  -0.0417   0.9007   0.0060
  -5.000  -0.3459   0.01254   0.00629  -0.0410   0.8911   0.0062
  -4.750  -0.3220   0.01158   0.00516  -0.0403   0.8819   0.0068
  -4.250  -0.2706   0.01066   0.00406  -0.0394   0.8634   0.0081
  -4.000  -0.2442   0.01036   0.00369  -0.0391   0.8544   0.0093
  -3.750  -0.2177   0.01007   0.00329  -0.0387   0.8453   0.0102
  -3.500  -0.1909   0.00973   0.00285  -0.0384   0.8357   0.0122
  -3.250  -0.1643   0.00941   0.00253  -0.0381   0.8266   0.0218
  -3.000  -0.1379   0.00908   0.00227  -0.0379   0.8171   0.0492
  -2.750  -0.1115   0.00868   0.00205  -0.0378   0.8071   0.0989
  -2.500  -0.0850   0.00835   0.00187  -0.0376   0.7974   0.1509
  -2.250  -0.0590   0.00792   0.00169  -0.0375   0.7874   0.2336
  -2.000  -0.0325   0.00761   0.00156  -0.0374   0.7766   0.2990
  -1.750  -0.0062   0.00726   0.00144  -0.0373   0.7656   0.3802
  -1.500   0.0201   0.00695   0.00134  -0.0371   0.7540   0.4597
  -1.250   0.0462   0.00666   0.00125  -0.0368   0.7420   0.5412
  -1.000   0.0722   0.00643   0.00121  -0.0364   0.7298   0.6169
  -0.750   0.0982   0.00626   0.00119  -0.0359   0.7173   0.6793
  -0.500   0.1245   0.00617   0.00118  -0.0355   0.7045   0.7261
  -0.250   0.1510   0.00611   0.00117  -0.0351   0.6915   0.7627
   0.000   0.1774   0.00608   0.00118  -0.0346   0.6781   0.7941
   0.250   0.2037   0.00608   0.00119  -0.0341   0.6641   0.8213
   0.500   0.2299   0.00609   0.00120  -0.0336   0.6496   0.8451
   0.750   0.2559   0.00612   0.00122  -0.0330   0.6350   0.8671
   1.000   0.2817   0.00615   0.00125  -0.0324   0.6206   0.8888
   1.500   0.3344   0.00624   0.00132  -0.0314   0.5906   0.9312
   1.750   0.3641   0.00631   0.00136  -0.0317   0.5740   0.9498
   2.000   0.3967   0.00641   0.00140  -0.0327   0.5547   0.9656
   2.250   0.4311   0.00653   0.00146  -0.0341   0.5339   0.9786
   2.500   0.4659   0.00666   0.00151  -0.0357   0.5115   0.9892
   2.750   0.5001   0.00682   0.00159  -0.0373   0.4876   0.9989
   3.000   0.5259   0.00700   0.00168  -0.0370   0.4638   1.0000
   3.250   0.5508   0.00721   0.00181  -0.0365   0.4370   1.0000
   3.500   0.5758   0.00745   0.00195  -0.0361   0.4076   1.0000
   3.750   0.6004   0.00779   0.00211  -0.0356   0.3677   1.0000
   4.000   0.6238   0.00830   0.00234  -0.0351   0.3055   1.0000
   4.250   0.6476   0.00880   0.00261  -0.0346   0.2521   1.0000
   4.500   0.6715   0.00932   0.00289  -0.0342   0.2024   1.0000
   4.750   0.6961   0.00975   0.00316  -0.0339   0.1654   1.0000
   5.250   0.7452   0.01063   0.00380  -0.0332   0.1050   1.0000
   5.500   0.7691   0.01118   0.00418  -0.0327   0.0718   1.0000
   5.750   0.7921   0.01184   0.00466  -0.0322   0.0373   1.0000
   6.000   0.8156   0.01244   0.00515  -0.0317   0.0186   1.0000
   6.250   0.8405   0.01284   0.00557  -0.0313   0.0156   1.0000
   6.500   0.8652   0.01324   0.00602  -0.0309   0.0144   1.0000
   6.750   0.8896   0.01370   0.00655  -0.0304   0.0134   1.0000
   7.000   0.9136   0.01419   0.00712  -0.0299   0.0126   1.0000
   7.250   0.9366   0.01481   0.00782  -0.0293   0.0119   1.0000
   7.500   0.9586   0.01555   0.00866  -0.0285   0.0114   1.0000
   7.750   0.9810   0.01617   0.00937  -0.0278   0.0112   1.0000
   8.000   1.0031   0.01682   0.01010  -0.0271   0.0109   1.0000
   8.250   1.0249   0.01747   0.01084  -0.0264   0.0104   1.0000
   8.500   1.0458   0.01821   0.01169  -0.0256   0.0099   1.0000
   8.750   1.0655   0.01905   0.01263  -0.0246   0.0096   1.0000
   9.000   1.0844   0.01996   0.01364  -0.0235   0.0093   1.0000
   9.250   1.1029   0.02087   0.01465  -0.0224   0.0089   1.0000
   9.500   1.1207   0.02180   0.01567  -0.0213   0.0085   1.0000
   9.750   1.1381   0.02271   0.01666  -0.0201   0.0081   1.0000
  10.000   1.1530   0.02384   0.01787  -0.0188   0.0077   1.0000
  10.250   1.1592   0.02602   0.02024  -0.0165   0.0071   1.0000
  10.500   1.1727   0.02713   0.02149  -0.0149   0.0069   1.0000
  10.750   1.1834   0.02819   0.02269  -0.0129   0.0068   1.0000
  11.000   1.1925   0.02928   0.02392  -0.0108   0.0066   1.0000
  11.250   1.2002   0.03050   0.02529  -0.0088   0.0063   1.0000
  11.500   1.2054   0.03204   0.02699  -0.0069   0.0060   1.0000
  11.750   1.2112   0.03345   0.02854  -0.0053   0.0057   1.0000
  12.000   1.2142   0.03525   0.03049  -0.0038   0.0055   1.0000
  12.250   1.2181   0.03695   0.03231  -0.0027   0.0052   1.0000
  12.500   1.2233   0.03854   0.03400  -0.0020   0.0050   1.0000
  12.750   1.2299   0.04003   0.03555  -0.0016   0.0047   1.0000
  13.000   1.2266   0.04293   0.03862  -0.0012   0.0047   1.0000
  13.250   1.2275   0.04539   0.04120  -0.0014   0.0046   1.0000
  13.500   1.2275   0.04811   0.04402  -0.0019   0.0044   1.0000
  13.750   1.2179   0.05241   0.04851  -0.0029   0.0044   1.0000
  14.000   1.2092   0.05680   0.05303  -0.0046   0.0042   1.0000
  14.250   1.1960   0.06221   0.05861  -0.0069   0.0042   1.0000
  14.500   1.1816   0.06824   0.06481  -0.0099   0.0042   1.0000
  14.750   1.1659   0.07491   0.07165  -0.0135   0.0042   1.0000
  15.000   1.1507   0.08200   0.07891  -0.0176   0.0042   1.0000
  15.250   1.1307   0.09047   0.08754  -0.0225   0.0042   1.0000
  15.500   1.1148   0.09867   0.09591  -0.0275   0.0042   1.0000
  15.750   1.0958   0.10777   0.10514  -0.0329   0.0042   1.0000
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