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S3010-103-84 (s3010-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: S3010-103-84 (s3010-il)
Reynolds number: 500,000
Max Cl/Cd: 89.19 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s3010-il-500000-n5.txt
Download as CSV file: xf-s3010-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S3010-103-84                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4673   0.08388   0.08161  -0.0209   1.0000   0.0097
  -9.250  -0.4746   0.07811   0.07588  -0.0241   1.0000   0.0096
  -9.000  -0.4879   0.07135   0.06916  -0.0283   1.0000   0.0095
  -8.750  -0.6080   0.03479   0.03182  -0.0558   0.9939   0.0089
  -8.500  -0.5928   0.02824   0.02456  -0.0601   0.9639   0.0090
  -8.250  -0.5729   0.02502   0.02087  -0.0612   0.9454   0.0092
  -7.750  -0.5337   0.02124   0.01641  -0.0601   0.9141   0.0095
  -7.500  -0.5123   0.01985   0.01473  -0.0593   0.9007   0.0097
  -7.250  -0.4896   0.01868   0.01331  -0.0587   0.8884   0.0098
  -7.000  -0.4659   0.01768   0.01209  -0.0581   0.8769   0.0100
  -6.750  -0.4416   0.01684   0.01105  -0.0575   0.8657   0.0101
  -6.500  -0.4165   0.01609   0.01013  -0.0571   0.8544   0.0103
  -6.250  -0.3911   0.01537   0.00925  -0.0566   0.8435   0.0104
  -6.000  -0.3665   0.01436   0.00812  -0.0562   0.8328   0.0107
  -5.750  -0.3407   0.01377   0.00745  -0.0559   0.8220   0.0112
  -5.500  -0.3144   0.01326   0.00685  -0.0556   0.8109   0.0116
  -5.250  -0.2878   0.01279   0.00629  -0.0553   0.8002   0.0119
  -5.000  -0.2613   0.01231   0.00571  -0.0550   0.7895   0.0123
  -4.750  -0.2342   0.01186   0.00518  -0.0548   0.7784   0.0126
  -4.500  -0.2071   0.01148   0.00470  -0.0545   0.7676   0.0130
  -4.250  -0.1797   0.01114   0.00427  -0.0543   0.7569   0.0134
  -4.000  -0.1523   0.01081   0.00385  -0.0541   0.7456   0.0138
  -3.750  -0.1247   0.01048   0.00345  -0.0540   0.7347   0.0146
  -3.500  -0.0970   0.01024   0.00313  -0.0538   0.7236   0.0155
  -3.000  -0.0412   0.00984   0.00260  -0.0535   0.7008   0.0191
  -2.750  -0.0133   0.00962   0.00236  -0.0534   0.6896   0.0253
  -2.500   0.0144   0.00935   0.00215  -0.0533   0.6779   0.0496
  -2.000   0.0699   0.00889   0.00185  -0.0533   0.6538   0.1167
  -1.750   0.0976   0.00867   0.00174  -0.0533   0.6414   0.1625
  -1.500   0.1253   0.00842   0.00165  -0.0533   0.6288   0.2202
  -1.250   0.1529   0.00822   0.00158  -0.0532   0.6159   0.2782
  -1.000   0.1805   0.00802   0.00152  -0.0532   0.6029   0.3431
  -0.500   0.2356   0.00766   0.00147  -0.0531   0.5765   0.4769
  -0.250   0.2632   0.00755   0.00146  -0.0530   0.5636   0.5308
   0.000   0.2906   0.00744   0.00147  -0.0529   0.5505   0.5877
   0.250   0.3178   0.00735   0.00149  -0.0526   0.5376   0.6458
   0.500   0.3447   0.00727   0.00152  -0.0523   0.5242   0.7008
   0.750   0.3711   0.00721   0.00156  -0.0518   0.5107   0.7538
   1.000   0.3967   0.00716   0.00161  -0.0511   0.4971   0.8065
   1.250   0.4211   0.00711   0.00167  -0.0500   0.4838   0.8617
   1.500   0.4459   0.00708   0.00170  -0.0490   0.4711   0.9209
   1.750   0.4835   0.00713   0.00172  -0.0509   0.4570   0.9785
   2.000   0.5151   0.00725   0.00176  -0.0516   0.4436   1.0000
   2.250   0.5427   0.00739   0.00182  -0.0515   0.4310   1.0000
   2.500   0.5702   0.00754   0.00190  -0.0514   0.4180   1.0000
   2.750   0.5976   0.00770   0.00198  -0.0513   0.4050   1.0000
   3.000   0.6250   0.00787   0.00208  -0.0512   0.3912   1.0000
   3.250   0.6524   0.00804   0.00219  -0.0511   0.3773   1.0000
   3.500   0.6798   0.00822   0.00230  -0.0510   0.3631   1.0000
   3.750   0.7071   0.00840   0.00243  -0.0509   0.3492   1.0000
   4.000   0.7342   0.00860   0.00257  -0.0508   0.3350   1.0000
   4.250   0.7613   0.00881   0.00272  -0.0507   0.3205   1.0000
   4.500   0.7883   0.00903   0.00288  -0.0506   0.3060   1.0000
   4.750   0.8151   0.00927   0.00307  -0.0504   0.2912   1.0000
   5.000   0.8418   0.00951   0.00325  -0.0503   0.2771   1.0000
   5.250   0.8683   0.00978   0.00346  -0.0501   0.2621   1.0000
   5.500   0.8947   0.01005   0.00368  -0.0500   0.2477   1.0000
   5.750   0.9210   0.01033   0.00392  -0.0498   0.2338   1.0000
   6.000   0.9472   0.01062   0.00417  -0.0496   0.2209   1.0000
   6.250   0.9732   0.01093   0.00443  -0.0494   0.2074   1.0000
   6.500   0.9989   0.01126   0.00472  -0.0491   0.1945   1.0000
   6.750   1.0245   0.01160   0.00502  -0.0489   0.1816   1.0000
   7.000   1.0498   0.01196   0.00533  -0.0486   0.1695   1.0000
   7.250   1.0748   0.01234   0.00568  -0.0483   0.1568   1.0000
   7.500   1.0996   0.01273   0.00603  -0.0480   0.1444   1.0000
   7.750   1.1243   0.01311   0.00639  -0.0476   0.1334   1.0000
   8.000   1.1488   0.01352   0.00678  -0.0473   0.1230   1.0000
   8.250   1.1728   0.01395   0.00720  -0.0469   0.1138   1.0000
   8.500   1.1965   0.01440   0.00763  -0.0464   0.1052   1.0000
   8.750   1.2202   0.01483   0.00806  -0.0459   0.0969   1.0000
   9.000   1.2428   0.01535   0.00855  -0.0454   0.0873   1.0000
   9.250   1.2649   0.01591   0.00909  -0.0448   0.0781   1.0000
   9.500   1.2868   0.01644   0.00961  -0.0441   0.0702   1.0000
   9.750   1.3083   0.01699   0.01016  -0.0434   0.0633   1.0000
  10.000   1.3286   0.01762   0.01077  -0.0426   0.0565   1.0000
  10.250   1.3490   0.01820   0.01138  -0.0418   0.0509   1.0000
  10.500   1.3682   0.01884   0.01203  -0.0409   0.0458   1.0000
  10.750   1.3866   0.01951   0.01271  -0.0398   0.0412   1.0000
  11.000   1.4043   0.02018   0.01341  -0.0387   0.0376   1.0000
  11.250   1.4207   0.02089   0.01415  -0.0374   0.0339   1.0000
  11.500   1.4346   0.02166   0.01496  -0.0358   0.0307   1.0000
  11.750   1.4459   0.02241   0.01577  -0.0338   0.0278   1.0000
  12.000   1.4543   0.02336   0.01673  -0.0316   0.0247   1.0000
  12.250   1.4634   0.02431   0.01775  -0.0297   0.0222   1.0000
  12.500   1.4701   0.02550   0.01897  -0.0279   0.0194   1.0000
  12.750   1.4762   0.02681   0.02033  -0.0262   0.0165   1.0000
  13.000   1.4814   0.02828   0.02187  -0.0248   0.0142   1.0000
  13.250   1.4847   0.03001   0.02366  -0.0235   0.0123   1.0000
  13.500   1.4880   0.03187   0.02560  -0.0224   0.0108   1.0000
  13.750   1.4893   0.03402   0.02783  -0.0216   0.0098   1.0000
  14.000   1.4912   0.03625   0.03015  -0.0211   0.0091   1.0000
  14.250   1.4923   0.03869   0.03270  -0.0208   0.0086   1.0000
  14.500   1.4915   0.04145   0.03556  -0.0207   0.0082   1.0000
  14.750   1.4891   0.04455   0.03877  -0.0210   0.0078   1.0000
  15.000   1.4864   0.04782   0.04216  -0.0215   0.0077   1.0000
  15.250   1.4798   0.05173   0.04619  -0.0224   0.0074   1.0000
  15.500   1.4733   0.05580   0.05039  -0.0235   0.0072   1.0000
  15.750   1.4675   0.05992   0.05464  -0.0248   0.0070   1.0000
  16.000   1.4585   0.06472   0.05957  -0.0266   0.0069   1.0000
  16.250   1.4492   0.06974   0.06473  -0.0286   0.0068   1.0000
  16.500   1.4386   0.07516   0.07029  -0.0309   0.0067   1.0000
  16.750   1.4275   0.08085   0.07613  -0.0335   0.0066   1.0000
  17.000   1.4154   0.08685   0.08226  -0.0363   0.0065   1.0000
  17.250   1.4014   0.09340   0.08896  -0.0395   0.0064   1.0000
  17.500   1.3874   0.10012   0.09581  -0.0428   0.0064   1.0000
  17.750   1.3723   0.10718   0.10301  -0.0464   0.0064   1.0000
  18.000   1.3564   0.11460   0.11057  -0.0503   0.0063   1.0000
  18.250   1.3410   0.12204   0.11815  -0.0543   0.0063   1.0000
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