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NREL's S830 Airfoil (s830-nr) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NREL's S830 Airfoil (s830-nr)
Reynolds number: 200,000
Max Cl/Cd: 61.14 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s830-nr-200000.txt
Download as CSV file: xf-s830-nr-200000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.2659   0.11006   0.10666  -0.1009   0.9652   0.0424
 -11.500  -0.2863   0.10283   0.09933  -0.1087   0.9617   0.0426
 -11.250  -0.3046   0.09770   0.09410  -0.1126   0.9552   0.0426
 -11.000  -0.3141   0.09291   0.08922  -0.1165   0.9499   0.0426
 -10.750  -0.2655   0.08771   0.08422  -0.1158   0.9500   0.0448
 -10.500  -0.2642   0.08261   0.07905  -0.1206   0.9475   0.0456
 -10.250  -0.2793   0.07841   0.07479  -0.1220   0.9384   0.0459
 -10.000  -0.2843   0.07356   0.06982  -0.1262   0.9345   0.0468
  -9.750  -0.3002   0.07022   0.06639  -0.1265   0.9247   0.0472
  -9.500  -0.3050   0.06620   0.06221  -0.1298   0.9202   0.0483
  -9.250  -0.3237   0.06396   0.05986  -0.1279   0.9087   0.0487
  -9.000  -0.3375   0.06149   0.05723  -0.1271   0.8981   0.0498
  -8.750  -0.3434   0.06175   0.05678  -0.1295   0.8918   0.0529
  -8.250  -0.3294   0.05140   0.04638  -0.1292   0.8796   0.0557
  -8.000  -0.3024   0.04805   0.04293  -0.1318   0.8781   0.0583
  -7.750  -0.2997   0.04653   0.04124  -0.1293   0.8681   0.0610
  -7.500  -0.2789   0.04352   0.03775  -0.1314   0.8651   0.0677
  -7.250  -0.2446   0.04011   0.03433  -0.1343   0.8639   0.0713
  -7.000  -0.1933   0.03391   0.02715  -0.1323   0.8635   0.0332
  -6.750  -0.1459   0.03055   0.02332  -0.1323   0.8632   0.0275
  -6.500  -0.0932   0.02894   0.02166  -0.1316   0.8635   0.0273
  -6.250  -0.0184   0.02849   0.02125  -0.1335   0.8652   0.0293
  -6.000   0.0300   0.02799   0.02074  -0.1359   0.8637   0.0328
  -5.500   0.0691   0.02690   0.01971  -0.1336   0.8501   0.0443
  -5.250   0.0805   0.02623   0.01905  -0.1320   0.8422   0.0533
  -5.000   0.0793   0.02518   0.01803  -0.1291   0.8337   0.0616
  -4.750   0.0710   0.02426   0.01710  -0.1250   0.8231   0.0681
  -4.500   0.3060   0.04136   0.03585  -0.1330   0.8341   0.5957
  -4.250   0.3794   0.03972   0.03398  -0.1397   0.8319   0.6023
  -4.000   0.3902   0.03980   0.03399  -0.1375   0.8213   0.6093
  -3.750   0.3706   0.04012   0.03425  -0.1321   0.8104   0.6134
  -3.500   0.4064   0.03903   0.03303  -0.1342   0.8038   0.6141
  -3.250   0.4292   0.03833   0.03222  -0.1343   0.7965   0.6146
  -3.000   0.4504   0.03769   0.03149  -0.1341   0.7888   0.6151
  -2.750   0.4741   0.03705   0.03075  -0.1344   0.7823   0.6157
  -2.500   0.4908   0.03658   0.03022  -0.1333   0.7743   0.6166
  -2.250   0.5168   0.03596   0.02949  -0.1341   0.7684   0.6174
  -2.000   0.4638   0.03752   0.03111  -0.1222   0.7575   0.6279
  -1.750   0.4783   0.03680   0.03030  -0.1215   0.7513   0.6288
  -1.500   0.4948   0.03610   0.02958  -0.1199   0.7440   0.6292
  -1.250   0.5252   0.03531   0.02867  -0.1213   0.7390   0.6296
  -1.000   0.5387   0.03482   0.02819  -0.1192   0.7322   0.6303
  -0.750   0.5609   0.03426   0.02757  -0.1189   0.7263   0.6310
  -0.500   0.5901   0.03368   0.02690  -0.1202   0.7218   0.6318
  -0.250   0.5953   0.03346   0.02672  -0.1165   0.7146   0.6332
   0.000   0.6171   0.03303   0.02623  -0.1165   0.7094   0.6347
   0.250   0.6327   0.03274   0.02591  -0.1153   0.7041   0.6369
   0.500   0.6088   0.02886   0.02191  -0.1203   0.6962   0.5942
   0.750   0.6407   0.02827   0.02123  -0.1223   0.6921   0.5928
   1.000   0.6566   0.02767   0.02064  -0.1220   0.6864   0.5910
   1.250   0.6806   0.02696   0.01990  -0.1235   0.6811   0.5900
   1.500   0.7165   0.02628   0.01914  -0.1272   0.6772   0.5899
   1.750   0.7453   0.02575   0.01858  -0.1294   0.6727   0.5906
   2.000   0.7695   0.02524   0.01807  -0.1309   0.6673   0.5923
   2.250   0.8072   0.02459   0.01735  -0.1350   0.6630   0.5935
   2.500   0.8660   0.02343   0.01597  -0.1451   0.6596   0.5966
   2.750   0.8778   0.02346   0.01612  -0.1425   0.6542   0.5973
   3.000   0.9001   0.02347   0.01617  -0.1420   0.6499   0.5981
   3.250   0.9300   0.02345   0.01617  -0.1429   0.6465   0.5990
   3.500   0.9655   0.02347   0.01616  -0.1449   0.6438   0.6002
   3.750   0.9777   0.02362   0.01644  -0.1427   0.6389   0.6014
   4.000   1.0009   0.02367   0.01657  -0.1426   0.6347   0.6031
   4.250   1.0329   0.02365   0.01655  -0.1442   0.6313   0.6053
   4.500   1.0737   0.02355   0.01641  -0.1479   0.6287   0.6079
   4.750   1.1005   0.02353   0.01645  -0.1495   0.6247   0.6109
   5.000   1.1255   0.02359   0.01657  -0.1503   0.6208   0.6131
   5.250   1.1495   0.02373   0.01680  -0.1501   0.6175   0.6142
   5.500   1.1798   0.02384   0.01697  -0.1510   0.6147   0.6155
   5.750   1.2163   0.02399   0.01715  -0.1532   0.6123   0.6170
   6.000   1.2229   0.02445   0.01781  -0.1500   0.6082   0.6187
   6.250   1.2425   0.02476   0.01824  -0.1494   0.6044   0.6207
   6.500   1.2725   0.02490   0.01844  -0.1506   0.6012   0.6235
   6.750   1.3128   0.02495   0.01850  -0.1541   0.5986   0.6273
   7.000   1.3432   0.02514   0.01878  -0.1554   0.5955   0.6295
   7.250   1.3451   0.02567   0.01951  -0.1512   0.5903   0.6307
   7.500   1.3686   0.02581   0.01977  -0.1508   0.5861   0.6324
   7.750   1.4186   0.02534   0.01927  -0.1551   0.5811   0.6346
   8.000   1.4128   0.02559   0.01971  -0.1493   0.5726   0.6364
   8.250   1.4468   0.02484   0.01891  -0.1504   0.5625   0.6392
   8.500   1.4588   0.02467   0.01880  -0.1479   0.5538   0.6418
   8.750   1.4800   0.02451   0.01867  -0.1471   0.5460   0.6445
   9.000   1.4871   0.02451   0.01879  -0.1435   0.5382   0.6462
   9.250   1.5009   0.02455   0.01893  -0.1411   0.5304   0.6482
   9.500   1.5090   0.02473   0.01923  -0.1379   0.5223   0.6504
   9.750   1.5191   0.02495   0.01954  -0.1353   0.5141   0.6528
  10.000   1.5308   0.02505   0.01970  -0.1329   0.5044   0.6553
  10.250   1.5297   0.02567   0.02045  -0.1287   0.4948   0.6576
  10.500   1.5373   0.02605   0.02088  -0.1260   0.4837   0.6598
  10.750   1.5420   0.02648   0.02138  -0.1227   0.4716   0.6615
  11.000   1.5343   0.02756   0.02262  -0.1180   0.4590   0.6630
  11.250   1.5301   0.02866   0.02383  -0.1140   0.4440   0.6648
  11.500   1.5247   0.03001   0.02524  -0.1102   0.4264   0.6668
  11.750   1.5146   0.03187   0.02718  -0.1062   0.4036   0.6688
  12.000   1.5021   0.03414   0.02938  -0.1024   0.3700   0.6709
  12.250   1.4813   0.03729   0.03229  -0.0983   0.3277   0.6726
  12.500   1.4559   0.04128   0.03601  -0.0944   0.2906   0.6740
  12.750   1.4320   0.04563   0.04015  -0.0914   0.2557   0.6753
  13.000   1.4092   0.05014   0.04450  -0.0889   0.2237   0.6762
  13.250   1.3882   0.05479   0.04901  -0.0869   0.1941   0.6771
  13.500   1.3692   0.05953   0.05361  -0.0854   0.1664   0.6782
  13.750   1.3523   0.06428   0.05822  -0.0844   0.1417   0.6792
  14.000   1.3387   0.06883   0.06267  -0.0837   0.1194   0.6805
  14.500   1.3187   0.07754   0.07122  -0.0830   0.0882   0.6833
  15.000   1.3092   0.08537   0.07901  -0.0831   0.0678   0.6871
  15.250   1.3080   0.08897   0.08264  -0.0833   0.0603   0.6892
  15.500   1.3034   0.09298   0.08656  -0.0836   0.0545   0.6910
  15.750   1.3069   0.09593   0.08966  -0.0838   0.0490   0.6928
  16.000   1.3047   0.09947   0.09316  -0.0840   0.0446   0.6945
  16.250   1.3093   0.10235   0.09619  -0.0844   0.0404   0.6966
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