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NREL's S814 Airfoil (s814-nr) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NREL's S814 Airfoil (s814-nr)
Reynolds number: 100,000
Max Cl/Cd: 40.14 at α=9.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s814-nr-100000-n5.txt
Download as CSV file: xf-s814-nr-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S814 Airfoil                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.1705   0.10748   0.09970  -0.0389   0.9824   0.2912
  -8.000  -0.1495   0.10491   0.09710  -0.0422   0.9775   0.2926
  -7.750  -0.1317   0.10230   0.09446  -0.0452   0.9713   0.2942
  -7.500  -0.1307   0.09889   0.09098  -0.0493   0.9656   0.2989
  -7.250  -0.1019   0.09727   0.08939  -0.0507   0.9572   0.2998
  -7.000  -0.0723   0.09526   0.08737  -0.0536   0.9516   0.3007
  -6.750  -0.0540   0.09340   0.08552  -0.0545   0.9403   0.3014
  -6.500  -0.0374   0.09161   0.08375  -0.0551   0.9275   0.3023
  -6.250  -0.0216   0.08985   0.08200  -0.0557   0.9133   0.3032
  -6.000  -0.0062   0.08799   0.08015  -0.0564   0.8985   0.3042
  -5.750   0.0121   0.08613   0.07829  -0.0577   0.8847   0.3058
  -5.500   0.0321   0.08398   0.07611  -0.0598   0.8724   0.3080
  -5.250   0.0525   0.08142   0.07350  -0.0629   0.8606   0.3095
  -5.000   0.0721   0.07870   0.07071  -0.0662   0.8467   0.3105
  -4.750   0.0917   0.07565   0.06757  -0.0705   0.8327   0.3117
  -4.500   0.1096   0.07219   0.06398  -0.0760   0.8179   0.3139
  -4.250   0.1615   0.07052   0.06223  -0.0814   0.8020   0.3149
  -4.000   0.2058   0.06885   0.06046  -0.0861   0.7838   0.3159
  -3.750   0.2412   0.06723   0.05871  -0.0898   0.7645   0.3169
  -3.500   0.2669   0.06558   0.05694  -0.0923   0.7456   0.3176
  -3.250   0.2878   0.06407   0.05533  -0.0940   0.7281   0.3183
  -3.000   0.3055   0.06266   0.05382  -0.0950   0.7119   0.3189
  -2.750   0.3213   0.06131   0.05240  -0.0957   0.6974   0.3197
  -2.500   0.3352   0.05997   0.05098  -0.0962   0.6848   0.3206
  -2.250   0.3467   0.05866   0.04961  -0.0962   0.6731   0.3216
  -2.000   0.3546   0.05736   0.04828  -0.0958   0.6627   0.3232
  -1.750   0.3569   0.05571   0.04655  -0.0955   0.6538   0.3253
  -1.500   0.3482   0.05358   0.04440  -0.0942   0.6453   0.3268
  -1.250   0.3112   0.04991   0.04066  -0.0917   0.6387   0.3288
  -1.000   0.3282   0.04936   0.04011  -0.0908   0.6309   0.3294
  -0.750   0.3426   0.04876   0.03952  -0.0898   0.6232   0.3300
  -0.500   0.3575   0.04805   0.03879  -0.0891   0.6166   0.3307
  -0.250   0.3681   0.04731   0.03808  -0.0879   0.6093   0.3316
   0.000   0.3804   0.04643   0.03718  -0.0872   0.6032   0.3326
   0.250   0.3910   0.04552   0.03629  -0.0865   0.5974   0.3340
   0.500   0.3986   0.04443   0.03523  -0.0859   0.5916   0.3360
   0.750   0.3663   0.03429   0.02471  -0.0973   0.5878   0.3460
   1.250   0.4141   0.03332   0.02376  -0.0984   0.5780   0.3483
   1.500   0.4383   0.03263   0.02308  -0.0994   0.5730   0.3500
   1.750   0.4665   0.03163   0.02201  -0.1017   0.5686   0.3523
   2.000   0.5028   0.02931   0.01943  -0.1083   0.5641   0.3582
   2.250   0.5323   0.02847   0.01854  -0.1107   0.5590   0.3610
   2.500   0.5584   0.02851   0.01866  -0.1106   0.5547   0.3620
   2.750   0.5870   0.02851   0.01871  -0.1110   0.5512   0.3633
   3.000   0.6167   0.02848   0.01870  -0.1117   0.5480   0.3647
   3.250   0.6412   0.02841   0.01874  -0.1118   0.5437   0.3663
   3.500   0.6688   0.02827   0.01865  -0.1125   0.5395   0.3683
   3.750   0.7003   0.02802   0.01839  -0.1141   0.5357   0.3708
   4.000   0.7362   0.02766   0.01794  -0.1166   0.5326   0.3739
   4.250   0.7687   0.02743   0.01767  -0.1186   0.5293   0.3767
   4.500   0.7906   0.02766   0.01809  -0.1177   0.5253   0.3781
   4.750   0.8151   0.02786   0.01843  -0.1173   0.5214   0.3796
   5.000   0.8428   0.02803   0.01870  -0.1174   0.5179   0.3816
   5.250   0.8743   0.02815   0.01886  -0.1183   0.5148   0.3841
   5.500   0.8974   0.02833   0.01916  -0.1180   0.5103   0.3869
   5.750   0.9228   0.02843   0.01934  -0.1182   0.5055   0.3902
   6.000   0.9537   0.02843   0.01933  -0.1193   0.5012   0.3934
   6.250   0.9840   0.02855   0.01953  -0.1196   0.4975   0.3952
   6.500   1.0019   0.02889   0.02008  -0.1182   0.4923   0.3969
   6.750   1.0225   0.02912   0.02047  -0.1171   0.4867   0.3991
   7.000   1.0529   0.02913   0.02051  -0.1176   0.4814   0.4019
   7.250   1.0734   0.02932   0.02081  -0.1166   0.4751   0.4048
   7.500   1.0957   0.02940   0.02095  -0.1160   0.4678   0.4085
   7.750   1.1248   0.02933   0.02091  -0.1161   0.4612   0.4114
   8.000   1.1338   0.02968   0.02150  -0.1131   0.4531   0.4134
   8.250   1.1617   0.02956   0.02139  -0.1128   0.4456   0.4166
   8.500   1.1676   0.02995   0.02200  -0.1095   0.4369   0.4193
   8.750   1.1921   0.02982   0.02186  -0.1088   0.4286   0.4233
   9.000   1.1950   0.03023   0.02241  -0.1052   0.4197   0.4264
   9.250   1.2134   0.03023   0.02248  -0.1035   0.4110   0.4288
   9.500   1.2140   0.03093   0.02342  -0.0997   0.4008   0.4308
   9.750   1.2240   0.03134   0.02395  -0.0972   0.3904   0.4334
  10.000   1.2315   0.03188   0.02459  -0.0946   0.3786   0.4364
  10.250   1.2326   0.03283   0.02569  -0.0915   0.3651   0.4394
  10.500   1.2343   0.03387   0.02683  -0.0889   0.3500   0.4428
  10.750   1.2340   0.03508   0.02814  -0.0861   0.3327   0.4453
  11.000   1.2324   0.03647   0.02957  -0.0835   0.3125   0.4476
  11.250   1.2282   0.03826   0.03133  -0.0811   0.2899   0.4501
  11.500   1.2210   0.04051   0.03347  -0.0789   0.2681   0.4527
  11.750   1.2111   0.04331   0.03618  -0.0772   0.2482   0.4553
  12.000   1.2005   0.04654   0.03936  -0.0760   0.2294   0.4579
  12.250   1.1899   0.05009   0.04284  -0.0753   0.2122   0.4605
  12.500   1.1792   0.05380   0.04656  -0.0749   0.1968   0.4622
  12.750   1.1693   0.05764   0.05041  -0.0747   0.1827   0.4641
  13.000   1.1604   0.06155   0.05431  -0.0748   0.1696   0.4663
  13.250   1.1542   0.06534   0.05811  -0.0751   0.1570   0.4688
  13.500   1.1499   0.06904   0.06184  -0.0756   0.1454   0.4718
  13.750   1.1467   0.07274   0.06552  -0.0762   0.1351   0.4751
  14.000   1.1433   0.07652   0.06926  -0.0769   0.1257   0.4783
  14.250   1.1433   0.07992   0.07275  -0.0775   0.1164   0.4811
  14.500   1.1425   0.08346   0.07630  -0.0782   0.1089   0.4841
  14.750   1.1437   0.08686   0.07976  -0.0790   0.1013   0.4878
  15.000   1.1451   0.09029   0.08318  -0.0799   0.0950   0.4918
  15.250   1.1477   0.09362   0.08656  -0.0808   0.0888   0.4957
  15.500   1.1489   0.09706   0.09001  -0.0817   0.0839   0.4989
  15.750   1.1534   0.10018   0.09326  -0.0826   0.0785   0.5032
  16.000   1.1551   0.10370   0.09678  -0.0838   0.0744   0.5077
  16.250   1.1600   0.10678   0.09992  -0.0847   0.0704   0.5127
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