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NREL's S830 Airfoil (s830-nr) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NREL's S830 Airfoil (s830-nr)
Reynolds number: 500,000
Max Cl/Cd: 95.25 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s830-nr-500000.txt
Download as CSV file: xf-s830-nr-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.0419   0.08659   0.08430  -0.1332   0.9611   0.0183
 -12.250  -0.0324   0.08304   0.08074  -0.1359   0.9605   0.0189
 -12.000  -0.0596   0.07252   0.07018  -0.1412   0.9579   0.0186
  -8.500  -0.1072   0.01064   0.00549  -0.1552   0.8778   0.0144
  -8.250  -0.1384   0.02488   0.01940  -0.1562   0.8816   0.0140
  -8.000  -0.0680   0.02363   0.01809  -0.1576   0.8846   0.0129
  -7.750  -0.0223   0.02342   0.01774  -0.1578   0.8803   0.0126
  -7.500   0.0112   0.02329   0.01750  -0.1578   0.8722   0.0127
  -7.250   0.0405   0.02306   0.01716  -0.1580   0.8626   0.0128
  -7.000   0.0571   0.02273   0.01675  -0.1567   0.8505   0.0130
  -6.750   0.0698   0.02229   0.01622  -0.1551   0.8384   0.0136
  -6.500   0.0794   0.02174   0.01560  -0.1532   0.8272   0.0140
  -6.000   0.0808   0.02029   0.01405  -0.1471   0.8050   0.0156
  -5.750   0.0767   0.01962   0.01333  -0.1431   0.7948   0.0164
  -5.500   0.0748   0.01875   0.01236  -0.1401   0.7852   0.0183
  -5.250   0.0752   0.01767   0.01126  -0.1378   0.7756   0.0229
  -5.000   0.0884   0.01644   0.01001  -0.1384   0.7677   0.0309
  -4.750   0.1069   0.01536   0.00891  -0.1395   0.7596   0.0409
  -4.500   0.1365   0.01400   0.00752  -0.1435   0.7530   0.0610
  -4.250   0.1929   0.00941   0.00406  -0.1593   0.7455   0.4722
  -4.000   0.2224   0.00970   0.00428  -0.1597   0.7392   0.4933
  -3.750   0.2503   0.00999   0.00446  -0.1598   0.7323   0.5044
  -3.500   0.2762   0.01042   0.00489  -0.1592   0.7256   0.5113
  -3.250   0.3048   0.01080   0.00514  -0.1595   0.7193   0.5187
  -3.000   0.3290   0.01110   0.00549  -0.1586   0.7125   0.5225
  -2.500   0.3811   0.01167   0.00599  -0.1579   0.7003   0.5284
  -2.250   0.4086   0.01178   0.00601  -0.1581   0.6942   0.5313
  -2.000   0.4374   0.01183   0.00594  -0.1587   0.6885   0.5336
  -1.750   0.4643   0.01171   0.00575  -0.1591   0.6823   0.5344
  -1.500   0.4922   0.01164   0.00560  -0.1595   0.6768   0.5352
  -1.250   0.5187   0.01159   0.00552  -0.1596   0.6710   0.5360
  -1.000   0.5449   0.01157   0.00546  -0.1597   0.6650   0.5367
  -0.500   0.5984   0.01159   0.00541  -0.1600   0.6538   0.5383
  -0.250   0.6249   0.01161   0.00539  -0.1601   0.6484   0.5392
   0.000   0.6536   0.01168   0.00538  -0.1607   0.6435   0.5402
   0.250   0.6788   0.01168   0.00539  -0.1605   0.6382   0.5413
   0.500   0.7054   0.01170   0.00538  -0.1607   0.6330   0.5425
   0.750   0.7344   0.01178   0.00538  -0.1614   0.6284   0.5438
   1.000   0.7601   0.01179   0.00539  -0.1614   0.6236   0.5452
   1.250   0.7864   0.01182   0.00540  -0.1615   0.6187   0.5466
   1.500   0.8146   0.01190   0.00541  -0.1620   0.6141   0.5481
   1.750   0.8418   0.01198   0.00546  -0.1623   0.6096   0.5493
   2.000   0.8666   0.01195   0.00546  -0.1621   0.6049   0.5507
   2.250   0.8926   0.01202   0.00553  -0.1621   0.6007   0.5519
   2.500   0.9224   0.01216   0.00564  -0.1630   0.5968   0.5530
   2.750   0.9456   0.01221   0.00575  -0.1624   0.5928   0.5542
   3.000   0.9700   0.01228   0.00586  -0.1621   0.5888   0.5554
   3.250   0.9963   0.01238   0.00596  -0.1622   0.5851   0.5568
   3.500   1.0270   0.01255   0.00609  -0.1632   0.5815   0.5583
   3.750   1.0507   0.01262   0.00621  -0.1628   0.5779   0.5599
   4.000   1.0746   0.01270   0.00632  -0.1625   0.5740   0.5615
   4.250   1.1005   0.01281   0.00643  -0.1625   0.5706   0.5631
   4.500   1.1297   0.01296   0.00657  -0.1633   0.5675   0.5645
   4.750   1.1605   0.01310   0.00671  -0.1644   0.5644   0.5660
   5.000   1.1828   0.01317   0.00688  -0.1637   0.5614   0.5674
   5.250   1.2068   0.01328   0.00707  -0.1634   0.5582   0.5687
   5.500   1.2318   0.01341   0.00725  -0.1632   0.5550   0.5702
   5.750   1.2598   0.01358   0.00745  -0.1637   0.5521   0.5718
   6.000   1.2934   0.01383   0.00772  -0.1654   0.5494   0.5736
   6.250   1.3141   0.01395   0.00794  -0.1644   0.5468   0.5754
   6.500   1.3360   0.01409   0.00815  -0.1637   0.5434   0.5773
   6.750   1.3554   0.01423   0.00832  -0.1624   0.5383   0.5790
   7.000   1.3700   0.01441   0.00850  -0.1602   0.5304   0.5803
   7.250   1.3797   0.01453   0.00865  -0.1570   0.5212   0.5818
   7.500   1.3946   0.01473   0.00891  -0.1550   0.5139   0.5833
   7.750   1.4099   0.01494   0.00919  -0.1530   0.5071   0.5847
   8.000   1.4269   0.01520   0.00950  -0.1514   0.5002   0.5862
   8.250   1.4423   0.01545   0.00985  -0.1495   0.4937   0.5877
   8.500   1.4599   0.01577   0.01017  -0.1481   0.4871   0.5894
   8.750   1.4745   0.01607   0.01059  -0.1462   0.4796   0.5912
   9.250   1.5029   0.01687   0.01149  -0.1424   0.4625   0.5948
   9.500   1.5151   0.01738   0.01203  -0.1402   0.4528   0.5963
   9.750   1.5246   0.01796   0.01264  -0.1377   0.4404   0.5981
  10.000   1.5318   0.01869   0.01341  -0.1349   0.4235   0.5996
  10.250   1.5343   0.01969   0.01440  -0.1315   0.3987   0.6010
  10.500   1.5264   0.02131   0.01590  -0.1269   0.3633   0.6022
  10.750   1.5064   0.02386   0.01821  -0.1211   0.3177   0.6033
  11.000   1.4883   0.02664   0.02079  -0.1161   0.2792   0.6044
  11.250   1.4700   0.02973   0.02369  -0.1117   0.2425   0.6055
  11.500   1.4562   0.03277   0.02659  -0.1081   0.2106   0.6067
  11.750   1.4436   0.03592   0.02961  -0.1051   0.1819   0.6079
  12.000   1.4329   0.03911   0.03268  -0.1026   0.1565   0.6091
  12.250   1.4244   0.04227   0.03575  -0.1005   0.1338   0.6104
  12.500   1.4165   0.04552   0.03891  -0.0987   0.1143   0.6115
  12.750   1.4117   0.04863   0.04196  -0.0973   0.0971   0.6125
  13.000   1.4076   0.05175   0.04505  -0.0961   0.0822   0.6141
  13.250   1.4048   0.05480   0.04810  -0.0951   0.0702   0.6154
  13.500   1.4032   0.05783   0.05113  -0.0943   0.0602   0.6167
  13.750   1.4023   0.06087   0.05418  -0.0936   0.0519   0.6181
  14.000   1.4007   0.06405   0.05736  -0.0931   0.0448   0.6194
  14.250   1.4025   0.06689   0.06024  -0.0927   0.0395   0.6208
  14.500   1.4035   0.06988   0.06327  -0.0924   0.0348   0.6222
  14.750   1.4046   0.07292   0.06633  -0.0922   0.0305   0.6237
  15.000   1.4072   0.07583   0.06929  -0.0921   0.0271   0.6252
  15.250   1.4083   0.07895   0.07242  -0.0921   0.0240   0.6266
  15.500   1.4114   0.08186   0.07539  -0.0922   0.0215   0.6280
  15.750   1.4136   0.08490   0.07848  -0.0924   0.0191   0.6296
  16.000   1.4167   0.08789   0.08156  -0.0926   0.0171   0.6313
  16.250   1.4201   0.09084   0.08457  -0.0929   0.0154   0.6329
  16.500   1.4201   0.09429   0.08809  -0.0932   0.0140   0.6344
  16.750   1.4241   0.09722   0.09112  -0.0936   0.0128   0.6360
  17.000   1.4261   0.10042   0.09438  -0.0941   0.0118   0.6377
  17.250   1.4254   0.10406   0.09810  -0.0947   0.0108   0.6392
  17.500   1.4290   0.10708   0.10122  -0.0953   0.0099   0.6409
  17.750   1.4313   0.11032   0.10452  -0.0961   0.0091   0.6425
  18.000   1.4282   0.11435   0.10861  -0.0970   0.0084   0.6439
  18.250   1.4320   0.11743   0.11182  -0.0979   0.0077   0.6459
  18.500   1.4343   0.12070   0.11520  -0.0989   0.0069   0.6478
  18.750   1.4308   0.12486   0.11943  -0.1001   0.0063   0.6494
  19.000   1.4313   0.12845   0.12314  -0.1013   0.0058   0.6513
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