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NREL's S830 Airfoil (s830-nr) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NREL's S830 Airfoil (s830-nr)
Reynolds number: 50,000
Max Cl/Cd: 10.75 at α=15.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s830-nr-50000-n5.txt
Download as CSV file: xf-s830-nr-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.3804   0.11880   0.11242  -0.0744   0.9823   0.0427
 -11.000  -0.3750   0.11419   0.10780  -0.0772   0.9771   0.0424
 -10.750  -0.3720   0.10920   0.10277  -0.0809   0.9730   0.0419
 -10.500  -0.3771   0.10438   0.09793  -0.0835   0.9664   0.0414
 -10.250  -0.3837   0.09926   0.09272  -0.0872   0.9610   0.0410
 -10.000  -0.3970   0.09473   0.08812  -0.0891   0.9533   0.0405
  -9.750  -0.4069   0.09020   0.08347  -0.0920   0.9472   0.0399
  -9.500  -0.4242   0.08669   0.07986  -0.0924   0.9378   0.0397
  -9.250  -0.4381   0.08330   0.07631  -0.0931   0.9298   0.0392
  -9.000  -0.4536   0.08038   0.07324  -0.0929   0.9209   0.0390
  -8.750  -0.4694   0.07786   0.07057  -0.0916   0.9108   0.0385
  -8.500  -0.4763   0.07460   0.06707  -0.0920   0.9025   0.0384
  -8.250  -0.4790   0.07147   0.06365  -0.0917   0.8942   0.0382
  -8.000  -0.4803   0.06870   0.06062  -0.0908   0.8857   0.0379
  -7.750  -0.4710   0.06548   0.05705  -0.0911   0.8793   0.0376
  -7.500  -0.4650   0.06299   0.05426  -0.0900   0.8714   0.0375
  -7.250  -0.4492   0.06023   0.05117  -0.0900   0.8654   0.0374
  -7.000  -0.4223   0.05746   0.04803  -0.0908   0.8617   0.0376
  -6.750  -0.4126   0.05586   0.04622  -0.0883   0.8530   0.0380
  -6.500  -0.3831   0.05382   0.04389  -0.0885   0.8490   0.0393
  -6.250  -0.3585   0.05252   0.04225  -0.0870   0.8435   0.0415
  -6.000  -0.3239   0.05188   0.04152  -0.0844   0.8386   0.0442
  -5.750  -0.1691   0.05372   0.04323  -0.0871   0.8474   0.0570
  -5.500  -0.1516   0.05428   0.04373  -0.0835   0.8388   0.0626
  -5.250  -0.1226   0.05432   0.04382  -0.0821   0.8342   0.0714
  -5.000  -0.1170   0.05424   0.04366  -0.0788   0.8261   0.0785
  -4.750  -0.1137   0.05364   0.04315  -0.0760   0.8191   0.0861
  -4.500  -0.1218   0.05328   0.04277  -0.0716   0.8103   0.0924
  -4.250  -0.1291   0.05236   0.04192  -0.0679   0.8031   0.0997
  -4.000  -0.1444   0.05177   0.04136  -0.0631   0.7933   0.1069
  -3.750  -0.1493   0.04993   0.03964  -0.0613   0.7870   0.1221
  -3.500  -0.1652   0.04866   0.03850  -0.0580   0.7772   0.1353
  -3.250  -0.1549   0.04896   0.04005  -0.0582   0.7712   0.4943
  -3.000  -0.1426   0.05329   0.04417  -0.0518   0.7626   0.5444
  -2.750  -0.1108   0.05830   0.04896  -0.0432   0.7581   0.5930
  -2.500  -0.0756   0.06017   0.05058  -0.0399   0.7552   0.6278
  -2.250  -0.0771   0.06032   0.05065  -0.0363   0.7464   0.6299
  -2.000  -0.0631   0.05940   0.04951  -0.0367   0.7411   0.6287
  -1.750  -0.0356   0.05838   0.04822  -0.0384   0.7382   0.6275
  -1.500  -0.0451   0.05863   0.04842  -0.0349   0.7279   0.6271
  -1.250  -0.0198   0.05784   0.04743  -0.0360   0.7243   0.6264
  -1.000  -0.0162   0.05783   0.04732  -0.0347   0.7167   0.6266
  -0.750   0.0004   0.05746   0.04679  -0.0350   0.7113   0.6267
  -0.500   0.0283   0.05676   0.04591  -0.0368   0.7082   0.6268
  -0.250   0.0327   0.05703   0.04610  -0.0358   0.7003   0.6269
   0.000   0.0536   0.05674   0.04567  -0.0369   0.6954   0.6268
   0.250   0.0840   0.05614   0.04491  -0.0390   0.6924   0.6268
   0.500   0.0919   0.05663   0.04533  -0.0388   0.6855   0.6271
   0.750   0.1123   0.05666   0.04527  -0.0400   0.6805   0.6274
   1.000   0.1435   0.05629   0.04475  -0.0426   0.6774   0.6279
   1.250   0.1779   0.05581   0.04416  -0.0451   0.6752   0.6286
   1.500   0.1725   0.05721   0.04558  -0.0428   0.6659   0.6294
   1.750   0.1980   0.05723   0.04553  -0.0439   0.6626   0.6303
   2.000   0.2276   0.05711   0.04534  -0.0454   0.6603   0.6313
   2.250   0.2275   0.05855   0.04680  -0.0441   0.6525   0.6323
   2.500   0.2504   0.05887   0.04708  -0.0452   0.6484   0.6333
   2.750   0.2808   0.05887   0.04703  -0.0470   0.6456   0.6344
   3.250   0.3070   0.06098   0.04914  -0.0480   0.6351   0.6364
   3.500   0.3339   0.06136   0.04949  -0.0498   0.6317   0.6376
   3.750   0.3666   0.06149   0.04960  -0.0521   0.6293   0.6393
   4.000   0.3735   0.06318   0.05132  -0.0525   0.6230   0.6408
   4.250   0.3936   0.06428   0.05243  -0.0542   0.6185   0.6429
   4.500   0.4213   0.06481   0.05297  -0.0561   0.6154   0.6447
   4.750   0.4492   0.06506   0.05326  -0.0569   0.6131   0.6462
   5.000   0.4452   0.06732   0.05560  -0.0557   0.6060   0.6474
   5.250   0.4633   0.06834   0.05667  -0.0562   0.6019   0.6489
   5.500   0.4904   0.06887   0.05725  -0.0575   0.5989   0.6507
   5.750   0.5227   0.06921   0.05765  -0.0594   0.5967   0.6524
   6.000   0.5153   0.07198   0.06050  -0.0586   0.5884   0.6537
   6.250   0.5412   0.07283   0.06141  -0.0603   0.5846   0.6557
   6.500   0.5752   0.07336   0.06201  -0.0628   0.5819   0.6584
   6.750   0.5760   0.07581   0.06455  -0.0628   0.5744   0.6601
   7.000   0.5936   0.07683   0.06568  -0.0629   0.5697   0.6618
   7.250   0.6207   0.07738   0.06633  -0.0637   0.5667   0.6639
   7.500   0.6224   0.07962   0.06869  -0.0632   0.5592   0.6656
   7.750   0.6421   0.08080   0.07000  -0.0640   0.5540   0.6677
   8.000   0.6735   0.08136   0.07067  -0.0657   0.5508   0.6703
   8.250   0.6751   0.08389   0.07331  -0.0658   0.5421   0.6720
   8.500   0.7019   0.08495   0.07449  -0.0677   0.5373   0.6745
   8.750   0.7346   0.08517   0.07487  -0.0688   0.5342   0.6769
   9.000   0.7279   0.08805   0.07789  -0.0680   0.5238   0.6783
   9.250   0.7572   0.08840   0.07839  -0.0687   0.5197   0.6809
   9.500   0.7575   0.09095   0.08111  -0.0685   0.5100   0.6828
   9.750   0.7864   0.09149   0.08181  -0.0696   0.5049   0.6859
  10.000   0.7923   0.09384   0.08429  -0.0701   0.4953   0.6882
  10.250   0.8217   0.09445   0.08508  -0.0715   0.4895   0.6912
  10.500   0.8256   0.09663   0.08743  -0.0712   0.4794   0.6928
  10.750   0.8526   0.09685   0.08786  -0.0715   0.4737   0.6953
  11.000   0.8562   0.09915   0.09033  -0.0715   0.4626   0.6973
  11.250   0.8890   0.09889   0.09030  -0.0721   0.4573   0.7009
  11.500   0.8922   0.10137   0.09293  -0.0724   0.4449   0.7032
  12.000   0.9325   0.10265   0.09464  -0.0729   0.4271   0.7090
  12.250   0.9370   0.10468   0.09686  -0.0727   0.4143   0.7112
  12.500   0.9476   0.10611   0.09851  -0.0727   0.4024   0.7138
  12.750   0.9841   0.10447   0.09713  -0.0727   0.3953   0.7179
  13.000   0.9936   0.10605   0.09891  -0.0731   0.3813   0.7207
  13.500   1.0155   0.10806   0.10137  -0.0726   0.3532   0.7261
  13.750   1.0305   0.10845   0.10201  -0.0723   0.3389   0.7295
  14.000   1.0493   0.10831   0.10211  -0.0720   0.3241   0.7333
  14.250   1.0720   0.10761   0.10165  -0.0718   0.3083   0.7375
  14.750   1.1085   0.10690   0.10135  -0.0704   0.2677   0.7446
  15.000   1.1319   0.10597   0.10043  -0.0697   0.2395   0.7492
  15.250   1.1466   0.10662   0.10092  -0.0694   0.2089   0.7533
  15.500   1.1512   0.10869   0.10280  -0.0692   0.1825   0.7563
  15.750   1.1517   0.11172   0.10569  -0.0696   0.1604   0.7594
  16.000   1.1520   0.11498   0.10876  -0.0703   0.1421   0.7627
  16.250   1.1527   0.11845   0.11216  -0.0713   0.1261   0.7660
  16.500   1.1542   0.12174   0.11541  -0.0722   0.1129   0.7692
  16.750   1.1563   0.12476   0.11835  -0.0730   0.1019   0.7725
  17.000   1.1599   0.12784   0.12153  -0.0739   0.0919   0.7761
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