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NREL's S830 Airfoil (s830-nr) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NREL's S830 Airfoil (s830-nr)
Reynolds number: 200,000
Max Cl/Cd: 66.33 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s830-nr-200000-n5.txt
Download as CSV file: xf-s830-nr-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S830 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.1965   0.09116   0.08738  -0.1206   0.9540   0.0134
 -11.750  -0.2062   0.08458   0.08074  -0.1250   0.9500   0.0131
 -11.500  -0.2167   0.07807   0.07413  -0.1300   0.9473   0.0128
 -11.250  -0.2373   0.07315   0.06913  -0.1309   0.9385   0.0127
 -10.750  -0.2669   0.06386   0.05958  -0.1341   0.9245   0.0122
 -10.500  -0.2774   0.05889   0.05439  -0.1363   0.9198   0.0120
 -10.000  -0.3223   0.04728   0.04196  -0.1322   0.8993   0.0107
  -9.750  -0.3173   0.04440   0.03888  -0.1325   0.8936   0.0106
  -9.500  -0.3153   0.04160   0.03582  -0.1314   0.8858   0.0106
  -9.250  -0.3016   0.03885   0.03279  -0.1315   0.8804   0.0106
  -9.000  -0.2738   0.03584   0.02940  -0.1327   0.8779   0.0106
  -8.750  -0.2486   0.03396   0.02726  -0.1324   0.8725   0.0106
  -8.500  -0.2101   0.03228   0.02528  -0.1328   0.8692   0.0108
  -8.250  -0.1704   0.03120   0.02408  -0.1343   0.8663   0.0111
  -8.000  -0.1278   0.03040   0.02315  -0.1364   0.8637   0.0115
  -7.750  -0.0948   0.02986   0.02253  -0.1370   0.8581   0.0121
  -7.500  -0.0620   0.02939   0.02197  -0.1376   0.8520   0.0129
  -7.250  -0.0260   0.02884   0.02129  -0.1393   0.8472   0.0137
  -7.000  -0.0079   0.02831   0.02073  -0.1385   0.8378   0.0144
  -6.750   0.0185   0.02760   0.01997  -0.1398   0.8308   0.0167
  -6.500   0.0314   0.02705   0.01938  -0.1386   0.8209   0.0186
  -6.250   0.0481   0.02645   0.01872  -0.1380   0.8127   0.0219
  -6.000   0.0567   0.02575   0.01800  -0.1363   0.8031   0.0241
  -5.750   0.0629   0.02516   0.01735  -0.1340   0.7941   0.0279
  -5.500   0.0681   0.02440   0.01656  -0.1319   0.7855   0.0324
  -5.250   0.0599   0.02379   0.01594  -0.1271   0.7756   0.0360
  -5.000   0.0684   0.02304   0.01512  -0.1257   0.7681   0.0427
  -4.750   0.0685   0.02212   0.01422  -0.1232   0.7592   0.0495
  -4.500   0.0820   0.02094   0.01297  -0.1237   0.7522   0.0617
  -4.250   0.0960   0.01949   0.01152  -0.1250   0.7442   0.0823
  -4.000   0.1514   0.01479   0.00788  -0.1423   0.7381   0.4752
  -3.750   0.1755   0.01554   0.00862  -0.1410   0.7311   0.4951
  -3.500   0.2044   0.01616   0.00911  -0.1409   0.7250   0.5073
  -3.250   0.2295   0.01690   0.00980  -0.1397   0.7188   0.5142
  -3.000   0.2567   0.01715   0.00992  -0.1398   0.7122   0.5208
  -2.750   0.2811   0.01810   0.01085  -0.1378   0.7069   0.5237
  -2.500   0.3042   0.01829   0.01099  -0.1370   0.7006   0.5259
  -2.250   0.3332   0.01800   0.01056  -0.1381   0.6949   0.5275
  -2.000   0.3646   0.01763   0.01002  -0.1399   0.6899   0.5292
  -1.750   0.3928   0.01722   0.00948  -0.1411   0.6836   0.5312
  -1.500   0.4261   0.01674   0.00880  -0.1436   0.6780   0.5337
  -1.250   0.4540   0.01664   0.00861  -0.1442   0.6726   0.5345
  -1.000   0.4792   0.01661   0.00853  -0.1441   0.6666   0.5352
  -0.750   0.5071   0.01659   0.00844  -0.1445   0.6617   0.5358
  -0.500   0.5340   0.01659   0.00839  -0.1448   0.6568   0.5366
  -0.250   0.5594   0.01659   0.00837  -0.1448   0.6514   0.5374
   0.000   0.5869   0.01661   0.00833  -0.1451   0.6467   0.5385
   0.250   0.6149   0.01663   0.00830  -0.1456   0.6423   0.5396
   0.500   0.6399   0.01664   0.00831  -0.1456   0.6370   0.5410
   0.750   0.6672   0.01665   0.00827  -0.1460   0.6321   0.5424
   1.250   0.7227   0.01662   0.00815  -0.1472   0.6228   0.5458
   1.500   0.7508   0.01659   0.00807  -0.1480   0.6182   0.5477
   1.750   0.7811   0.01658   0.00797  -0.1491   0.6143   0.5496
   2.000   0.8076   0.01667   0.00807  -0.1493   0.6105   0.5504
   2.250   0.8311   0.01676   0.00822  -0.1489   0.6061   0.5513
   2.500   0.8565   0.01687   0.00836  -0.1488   0.6021   0.5523
   2.750   0.8841   0.01697   0.00846  -0.1492   0.5985   0.5534
   3.000   0.9104   0.01709   0.00859  -0.1494   0.5948   0.5546
   3.250   0.9331   0.01720   0.00877  -0.1489   0.5904   0.5560
   3.500   0.9582   0.01731   0.00890  -0.1488   0.5865   0.5575
   3.750   0.9863   0.01743   0.00902  -0.1494   0.5833   0.5594
   4.000   1.0162   0.01756   0.00914  -0.1504   0.5804   0.5615
   4.250   1.0391   0.01768   0.00932  -0.1500   0.5767   0.5638
   4.500   1.0633   0.01782   0.00951  -0.1499   0.5731   0.5655
   4.750   1.0877   0.01798   0.00975  -0.1497   0.5698   0.5666
   5.000   1.1152   0.01815   0.00995  -0.1501   0.5668   0.5677
   5.250   1.1409   0.01834   0.01021  -0.1501   0.5638   0.5690
   5.500   1.1614   0.01855   0.01055  -0.1492   0.5604   0.5704
   5.750   1.1843   0.01876   0.01086  -0.1488   0.5573   0.5719
   6.000   1.2091   0.01897   0.01114  -0.1488   0.5544   0.5737
   6.250   1.2370   0.01916   0.01138  -0.1493   0.5516   0.5755
   6.500   1.2660   0.01936   0.01163  -0.1501   0.5489   0.5776
   6.750   1.2851   0.01966   0.01204  -0.1491   0.5456   0.5797
   7.000   1.3064   0.01995   0.01245  -0.1484   0.5425   0.5814
   7.250   1.3285   0.02022   0.01286  -0.1478   0.5393   0.5828
   7.500   1.3537   0.02044   0.01318  -0.1478   0.5361   0.5844
   7.750   1.3744   0.02072   0.01357  -0.1470   0.5317   0.5860
   8.000   1.3825   0.02106   0.01404  -0.1438   0.5239   0.5876
   8.250   1.3929   0.02132   0.01435  -0.1410   0.5139   0.5894
   8.500   1.4035   0.02158   0.01460  -0.1383   0.5025   0.5912
   8.750   1.4074   0.02212   0.01527  -0.1347   0.4920   0.5929
   9.000   1.4184   0.02259   0.01580  -0.1324   0.4826   0.5948
   9.250   1.4294   0.02310   0.01634  -0.1302   0.4726   0.5967
   9.500   1.4350   0.02380   0.01719  -0.1272   0.4618   0.5979
   9.750   1.4422   0.02452   0.01801  -0.1245   0.4506   0.5994
  10.000   1.4483   0.02535   0.01892  -0.1218   0.4382   0.6009
  10.250   1.4525   0.02633   0.01999  -0.1190   0.4237   0.6026
  10.500   1.4540   0.02754   0.02127  -0.1160   0.4045   0.6043
  10.750   1.4509   0.02909   0.02280  -0.1126   0.3777   0.6060
  11.000   1.4395   0.03129   0.02485  -0.1086   0.3413   0.6075
  11.250   1.4205   0.03430   0.02765  -0.1043   0.3058   0.6088
  11.500   1.4019   0.03766   0.03085  -0.1006   0.2732   0.6100
  11.750   1.3849   0.04123   0.03429  -0.0976   0.2434   0.6112
  12.250   1.3572   0.04856   0.04142  -0.0932   0.1902   0.6133
  12.500   1.3464   0.05221   0.04502  -0.0916   0.1674   0.6143
  12.750   1.3373   0.05587   0.04861  -0.0903   0.1460   0.6155
  13.000   1.3303   0.05944   0.05215  -0.0893   0.1274   0.6167
  13.250   1.3252   0.06291   0.05559  -0.0886   0.1104   0.6180
  13.500   1.3214   0.06633   0.05899  -0.0880   0.0955   0.6195
  13.750   1.3189   0.06968   0.06233  -0.0877   0.0826   0.6211
  14.000   1.3178   0.07297   0.06561  -0.0874   0.0717   0.6227
  14.250   1.3175   0.07620   0.06885  -0.0873   0.0627   0.6243
  14.500   1.3173   0.07947   0.07215  -0.0873   0.0550   0.6259
  14.750   1.3196   0.08249   0.07522  -0.0874   0.0484   0.6275
  15.000   1.3209   0.08568   0.07846  -0.0875   0.0433   0.6289
  15.250   1.3232   0.08875   0.08161  -0.0878   0.0388   0.6301
  15.500   1.3247   0.09196   0.08489  -0.0880   0.0352   0.6315
  15.750   1.3276   0.09502   0.08805  -0.0884   0.0318   0.6331
  16.250   1.3314   0.10146   0.09468  -0.0893   0.0265   0.6367
  16.500   1.3334   0.10473   0.09802  -0.0899   0.0242   0.6386
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