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NREL's S810 Airfoil (s810-nr) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NREL's S810 Airfoil (s810-nr)
Reynolds number: 200,000
Max Cl/Cd: 52.21 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s810-nr-200000-n5.txt
Download as CSV file: xf-s810-nr-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S810 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.4726   0.06808   0.06320  -0.0745   0.7755   0.0190
  -8.250  -0.5627   0.04409   0.03703  -0.0554   0.7612   0.0177
  -8.000  -0.5501   0.04066   0.03339  -0.0541   0.7600   0.0161
  -7.750  -0.5310   0.03770   0.03010  -0.0528   0.7590   0.0145
  -7.500  -0.4991   0.03440   0.02627  -0.0518   0.7581   0.0127
  -7.250  -0.4721   0.03272   0.02437  -0.0517   0.7569   0.0125
  -7.000  -0.4413   0.03099   0.02246  -0.0522   0.7558   0.0124
  -6.750  -0.3801   0.02807   0.01936  -0.0569   0.7553   0.0126
  -6.500  -0.3242   0.02660   0.01780  -0.0598   0.7547   0.0131
  -6.250  -0.2918   0.02590   0.01709  -0.0602   0.7536   0.0141
  -6.000  -0.2666   0.02540   0.01657  -0.0600   0.7522   0.0159
  -5.750  -0.2387   0.02491   0.01602  -0.0596   0.7510   0.0172
  -5.500  -0.2156   0.02438   0.01545  -0.0586   0.7499   0.0175
  -5.250  -0.1985   0.02375   0.01481  -0.0572   0.7488   0.0179
  -5.000  -0.1851   0.02306   0.01408  -0.0556   0.7477   0.0182
  -4.750  -0.1735   0.02231   0.01330  -0.0539   0.7466   0.0187
  -4.500  -0.1675   0.02132   0.01227  -0.0517   0.7455   0.0194
  -4.250  -0.1661   0.02019   0.01107  -0.0490   0.7445   0.0203
  -4.000  -0.1638   0.01939   0.01021  -0.0462   0.7432   0.0215
  -3.750  -0.1590   0.01884   0.00962  -0.0435   0.7418   0.0235
  -3.500  -0.1460   0.01843   0.00915  -0.0419   0.7404   0.0275
  -3.250  -0.1326   0.01798   0.00857  -0.0403   0.7388   0.0309
  -3.000  -0.1163   0.01759   0.00811  -0.0390   0.7375   0.0389
  -2.750  -0.1182   0.01611   0.00727  -0.0358   0.7360   0.2423
  -2.500  -0.1216   0.01479   0.00743  -0.0316   0.7347   0.5967
  -2.250  -0.0936   0.01572   0.00836  -0.0312   0.7338   0.6271
  -2.000  -0.0660   0.01617   0.00872  -0.0312   0.7330   0.6377
  -1.750  -0.0383   0.01669   0.00918  -0.0311   0.7321   0.6482
  -1.500  -0.0092   0.01731   0.00983  -0.0309   0.7313   0.6539
  -1.250   0.0184   0.01729   0.00974  -0.0314   0.7304   0.6555
  -1.000   0.0451   0.01728   0.00967  -0.0318   0.7294   0.6571
  -0.750   0.0709   0.01728   0.00964  -0.0321   0.7282   0.6590
  -0.500   0.0966   0.01725   0.00957  -0.0326   0.7268   0.6611
  -0.250   0.1225   0.01719   0.00945  -0.0330   0.7252   0.6631
   0.000   0.1490   0.01725   0.00951  -0.0334   0.7238   0.6640
   0.250   0.1756   0.01732   0.00960  -0.0337   0.7225   0.6649
   0.500   0.2025   0.01739   0.00967  -0.0340   0.7211   0.6659
   0.750   0.2296   0.01745   0.00976  -0.0343   0.7199   0.6671
   1.000   0.2569   0.01752   0.00984  -0.0347   0.7187   0.6684
   1.250   0.2846   0.01756   0.00989  -0.0352   0.7176   0.6698
   1.500   0.3126   0.01759   0.00993  -0.0358   0.7166   0.6712
   1.750   0.3390   0.01768   0.01004  -0.0361   0.7151   0.6727
   2.000   0.3616   0.01788   0.01031  -0.0360   0.7122   0.6743
   2.250   0.3864   0.01801   0.01048  -0.0362   0.7098   0.6760
   2.500   0.4126   0.01809   0.01061  -0.0365   0.7076   0.6776
   2.750   0.4396   0.01816   0.01074  -0.0368   0.7057   0.6787
   3.000   0.4677   0.01818   0.01083  -0.0372   0.7040   0.6798
   3.250   0.4969   0.01817   0.01088  -0.0378   0.7025   0.6810
   3.500   0.5187   0.01840   0.01125  -0.0373   0.6987   0.6822
   3.750   0.5418   0.01852   0.01147  -0.0370   0.6943   0.6835
   4.000   0.5713   0.01836   0.01138  -0.0375   0.6910   0.6849
   4.250   0.6053   0.01797   0.01101  -0.0386   0.6881   0.6863
   4.500   0.6250   0.01797   0.01117  -0.0375   0.6797   0.6880
   4.750   0.6619   0.01721   0.01041  -0.0388   0.6739   0.6898
   5.000   0.6825   0.01706   0.01038  -0.0378   0.6638   0.6916
   5.250   0.7075   0.01671   0.01015  -0.0373   0.6542   0.6927
   5.500   0.7328   0.01632   0.00989  -0.0367   0.6433   0.6939
   5.750   0.7525   0.01618   0.00993  -0.0355   0.6296   0.6952
   6.000   0.7667   0.01616   0.01006  -0.0333   0.6073   0.6966
   6.250   0.7941   0.01521   0.00890  -0.0323   0.5378   0.6980
   6.500   0.7948   0.01561   0.00863  -0.0273   0.4399   0.6997
   6.750   0.7849   0.01648   0.00918  -0.0212   0.3825   0.7016
   7.000   0.7763   0.01760   0.01004  -0.0160   0.3308   0.7037
   7.250   0.7716   0.01889   0.01108  -0.0120   0.2830   0.7057
   7.500   0.7700   0.02017   0.01219  -0.0086   0.2394   0.7071
   7.750   0.7710   0.02146   0.01334  -0.0059   0.1977   0.7085
   8.000   0.7749   0.02271   0.01443  -0.0037   0.1597   0.7100
   8.250   0.7812   0.02388   0.01547  -0.0018   0.1281   0.7116
   8.500   0.7894   0.02501   0.01648  -0.0002   0.1021   0.7132
   8.750   0.8001   0.02603   0.01746   0.0011   0.0835   0.7150
   9.000   0.8115   0.02704   0.01844   0.0022   0.0701   0.7168
   9.250   0.8234   0.02805   0.01945   0.0033   0.0603   0.7188
   9.500   0.8345   0.02911   0.02050   0.0044   0.0513   0.7205
   9.750   0.8474   0.03005   0.02147   0.0053   0.0431   0.7222
  10.000   0.8608   0.03098   0.02250   0.0061   0.0369   0.7240
  10.250   0.8724   0.03207   0.02361   0.0070   0.0309   0.7258
  10.500   0.8866   0.03301   0.02467   0.0078   0.0276   0.7278
  10.750   0.8989   0.03412   0.02585   0.0085   0.0232   0.7297
  11.000   0.9102   0.03535   0.02715   0.0094   0.0183   0.7318
  11.250   0.9212   0.03665   0.02845   0.0101   0.0146   0.7338
  11.500   0.9315   0.03795   0.02990   0.0111   0.0128   0.7354
  11.750   0.9420   0.03928   0.03131   0.0118   0.0107   0.7372
  12.000   0.9496   0.04092   0.03305   0.0128   0.0099   0.7392
  12.250   0.9575   0.04258   0.03487   0.0136   0.0093   0.7414
  12.500   0.9653   0.04430   0.03678   0.0144   0.0088   0.7439
  12.750   0.9726   0.04613   0.03875   0.0151   0.0083   0.7464
  13.000   0.9794   0.04803   0.04081   0.0157   0.0081   0.7487
  13.250   0.9854   0.05004   0.04298   0.0164   0.0078   0.7508
  13.500   0.9911   0.05211   0.04521   0.0168   0.0075   0.7531
  13.750   0.9948   0.05447   0.04773   0.0173   0.0072   0.7555
  14.000   0.9985   0.05691   0.05033   0.0176   0.0071   0.7580
  14.250   0.9988   0.05985   0.05343   0.0178   0.0069   0.7605
  14.500   0.9996   0.06280   0.05657   0.0179   0.0068   0.7628
  14.750   0.9968   0.06630   0.06029   0.0179   0.0067   0.7649
  15.000   0.9941   0.06992   0.06413   0.0177   0.0066   0.7673
  15.250   0.9898   0.07385   0.06830   0.0171   0.0066   0.7699
  15.500   0.9841   0.07812   0.07279   0.0161   0.0065   0.7726
  15.750   0.9749   0.08312   0.07804   0.0147   0.0065   0.7751
  16.000   0.9644   0.08849   0.08366   0.0129   0.0065   0.7775
  16.250   0.9524   0.09438   0.08980   0.0104   0.0065   0.7799
  16.500   0.9376   0.10111   0.09678   0.0072   0.0064   0.7824
  16.750   0.9237   0.10800   0.10386   0.0036   0.0065   0.7851
  17.000   0.9064   0.11608   0.11216  -0.0010   0.0065   0.7875
  17.250   0.8883   0.12489   0.12116  -0.0063   0.0065   0.7899
  17.500   0.8698   0.13428   0.13072  -0.0120   0.0066   0.7918
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