Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NREL's S835 Airfoil (s835-nr) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NREL's S835 Airfoil (s835-nr)
Reynolds number: 500,000
Max Cl/Cd: 65.15 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s835-nr-500000-n5.txt
Download as CSV file: xf-s835-nr-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S835 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -19.250  -1.0415   0.09354   0.08907  -0.0732   0.9961   0.0998
 -19.000  -1.0465   0.08981   0.08531  -0.0748   0.9956   0.1020
 -18.750  -1.0496   0.08632   0.08178  -0.0764   0.9952   0.1047
 -18.500  -1.0488   0.08315   0.07855  -0.0781   0.9946   0.1070
 -18.250  -1.0480   0.07998   0.07532  -0.0799   0.9940   0.1092
 -18.000  -1.0526   0.07631   0.07163  -0.0816   0.9935   0.1119
 -17.750  -1.0522   0.07328   0.06855  -0.0831   0.9930   0.1145
 -17.500  -1.0505   0.07039   0.06560  -0.0846   0.9925   0.1170
 -17.250  -1.0493   0.06747   0.06264  -0.0861   0.9920   0.1194
 -17.000  -1.0510   0.06415   0.05929  -0.0878   0.9916   0.1225
 -16.750  -1.0515   0.06143   0.05652  -0.0886   0.9905   0.1251
 -16.500  -1.0493   0.05908   0.05411  -0.0891   0.9894   0.1278
 -16.250  -1.0501   0.05625   0.05125  -0.0901   0.9881   0.1304
 -16.000  -1.0492   0.05355   0.04852  -0.0911   0.9869   0.1333
 -15.750  -1.0465   0.05108   0.04600  -0.0921   0.9857   0.1365
 -15.500  -1.0373   0.04912   0.04398  -0.0933   0.9845   0.1392
 -15.250  -1.0340   0.04649   0.04133  -0.0947   0.9833   0.1423
 -15.000  -1.0276   0.04419   0.03900  -0.0962   0.9822   0.1456
 -14.750  -1.0168   0.04220   0.03696  -0.0978   0.9811   0.1490
 -14.500  -1.0036   0.04040   0.03511  -0.0994   0.9802   0.1521
 -14.250  -0.9940   0.03821   0.03290  -0.1013   0.9794   0.1555
 -14.000  -0.9803   0.03632   0.03098  -0.1034   0.9786   0.1595
 -13.750  -0.9818   0.03493   0.02954  -0.1013   0.9745   0.1623
 -13.500  -0.9729   0.03332   0.02790  -0.1018   0.9720   0.1655
 -13.250  -0.9625   0.03162   0.02619  -0.1028   0.9699   0.1690
 -13.000  -0.9472   0.03017   0.02471  -0.1042   0.9683   0.1731
 -12.750  -0.9273   0.02901   0.02349  -0.1057   0.9671   0.1766
 -12.500  -0.9096   0.02756   0.02202  -0.1076   0.9660   0.1804
 -12.250  -0.8889   0.02625   0.02069  -0.1097   0.9651   0.1847
 -12.000  -0.8959   0.02528   0.01970  -0.1057   0.9579   0.1874
 -11.750  -0.8763   0.02440   0.01876  -0.1065   0.9556   0.1909
 -11.500  -0.8579   0.02319   0.01756  -0.1078   0.9537   0.1946
 -11.250  -0.8353   0.02217   0.01652  -0.1095   0.9523   0.1991
 -11.000  -0.8088   0.02135   0.01566  -0.1113   0.9513   0.2032
 -10.750  -0.8147   0.02071   0.01498  -0.1067   0.9429   0.2052
 -10.500  -0.7970   0.01976   0.01403  -0.1072   0.9399   0.2089
 -10.250  -0.7737   0.01892   0.01317  -0.1085   0.9381   0.2128
 -10.000  -0.7468   0.01824   0.01246  -0.1100   0.9368   0.2169
  -9.750  -0.7564   0.01769   0.01187  -0.1045   0.9267   0.2190
  -9.500  -0.7367   0.01703   0.01118  -0.1045   0.9237   0.2221
  -9.250  -0.7161   0.01626   0.01041  -0.1049   0.9215   0.2259
  -9.000  -0.7297   0.01568   0.00979  -0.0986   0.9101   0.2279
  -8.750  -0.7053   0.01515   0.00924  -0.0991   0.9075   0.2319
  -8.500  -0.6756   0.01475   0.00879  -0.1002   0.9058   0.2352
  -8.250  -0.6669   0.01440   0.00842  -0.0973   0.8983   0.2381
  -8.000  -0.6457   0.01399   0.00801  -0.0968   0.8937   0.2417
  -7.750  -0.6164   0.01361   0.00761  -0.0978   0.8912   0.2456
  -7.500  -0.5823   0.01327   0.00725  -0.0995   0.8894   0.2498
  -7.250  -0.5459   0.01297   0.00692  -0.1017   0.8880   0.2534
  -7.000  -0.5352   0.01271   0.00667  -0.0989   0.8796   0.2567
  -6.750  -0.5034   0.01240   0.00635  -0.1002   0.8763   0.2612
  -6.500  -0.4668   0.01213   0.00606  -0.1023   0.8738   0.2658
  -6.250  -0.4274   0.01190   0.00581  -0.1050   0.8718   0.2695
  -6.000  -0.3996   0.01164   0.00556  -0.1055   0.8670   0.2741
  -5.750  -0.3727   0.01142   0.00534  -0.1057   0.8613   0.2787
  -5.500  -0.3377   0.01122   0.00512  -0.1074   0.8573   0.2834
  -5.250  -0.3009   0.01103   0.00491  -0.1095   0.8540   0.2877
  -5.000  -0.2730   0.01083   0.00472  -0.1099   0.8486   0.2927
  -4.750  -0.2457   0.01068   0.00457  -0.1100   0.8423   0.2974
  -4.500  -0.2125   0.01054   0.00440  -0.1113   0.8373   0.3024
  -4.250  -0.1793   0.01038   0.00423  -0.1126   0.8329   0.3073
  -4.000  -0.1551   0.01025   0.00412  -0.1121   0.8262   0.3124
  -3.750  -0.1253   0.01014   0.00400  -0.1127   0.8201   0.3178
  -3.500  -0.0919   0.01005   0.00387  -0.1140   0.8150   0.3228
  -3.250  -0.0672   0.00992   0.00378  -0.1135   0.8086   0.3282
  -3.000  -0.0391   0.00982   0.00369  -0.1137   0.8021   0.3337
  -2.750  -0.0076   0.00976   0.00358  -0.1146   0.7962   0.3391
  -2.500   0.0185   0.00967   0.00352  -0.1143   0.7897   0.3443
  -2.250   0.0458   0.00959   0.00345  -0.1143   0.7825   0.3505
  -2.000   0.0763   0.00954   0.00337  -0.1149   0.7762   0.3563
  -1.750   0.1021   0.00950   0.00333  -0.1146   0.7694   0.3610
  -1.500   0.1293   0.00943   0.00328  -0.1145   0.7623   0.3667
  -1.000   0.1848   0.00937   0.00321  -0.1146   0.7493   0.3788
  -0.750   0.2117   0.00931   0.00319  -0.1144   0.7422   0.3847
  -0.250   0.2663   0.00928   0.00316  -0.1142   0.7289   0.3963
   0.000   0.2929   0.00926   0.00315  -0.1140   0.7213   0.4015
   0.250   0.3207   0.00926   0.00315  -0.1140   0.7145   0.4081
   0.500   0.3459   0.00925   0.00317  -0.1134   0.7067   0.4146
   0.750   0.3718   0.00927   0.00317  -0.1130   0.6980   0.4201
   1.000   0.3967   0.00926   0.00319  -0.1124   0.6890   0.4261
   1.250   0.4205   0.00929   0.00321  -0.1115   0.6791   0.4320
   1.500   0.4442   0.00932   0.00323  -0.1106   0.6697   0.4374
   1.750   0.4671   0.00934   0.00326  -0.1095   0.6593   0.4435
   2.000   0.4902   0.00938   0.00331  -0.1085   0.6492   0.4500
   2.250   0.5125   0.00944   0.00335  -0.1073   0.6380   0.4559
   2.500   0.5355   0.00950   0.00342  -0.1063   0.6273   0.4616
   2.750   0.5573   0.00959   0.00350  -0.1050   0.6151   0.4681
   3.000   0.5799   0.00968   0.00359  -0.1039   0.6027   0.4743
   3.250   0.6011   0.00982   0.00370  -0.1026   0.5894   0.4801
   3.500   0.6220   0.00996   0.00384  -0.1012   0.5749   0.4862
   3.750   0.6436   0.01011   0.00398  -0.0999   0.5599   0.4926
   4.000   0.6638   0.01030   0.00413  -0.0984   0.5432   0.4985
   4.250   0.6828   0.01051   0.00432  -0.0966   0.5248   0.5042
   4.500   0.7010   0.01076   0.00452  -0.0948   0.5040   0.5103
   4.750   0.7180   0.01106   0.00475  -0.0927   0.4805   0.5161
   5.000   0.7343   0.01141   0.00500  -0.0906   0.4564   0.5213
   5.250   0.7496   0.01179   0.00531  -0.0883   0.4311   0.5271
   5.500   0.7655   0.01219   0.00562  -0.0862   0.4031   0.5333
   5.750   0.7802   0.01266   0.00597  -0.0839   0.3743   0.5388
   6.000   0.7947   0.01315   0.00635  -0.0817   0.3455   0.5440
   6.250   0.8092   0.01366   0.00677  -0.0795   0.3175   0.5502
   6.500   0.8240   0.01420   0.00720  -0.0774   0.2906   0.5562
   6.750   0.8392   0.01474   0.00763  -0.0754   0.2654   0.5616
   7.000   0.8537   0.01531   0.00811  -0.0733   0.2412   0.5672
   7.250   0.8686   0.01589   0.00860  -0.0714   0.2180   0.5734
   7.500   0.8837   0.01648   0.00910  -0.0695   0.1962   0.5794
   8.000   0.9147   0.01764   0.01015  -0.0660   0.1620   0.5904
   8.250   0.9305   0.01823   0.01070  -0.0643   0.1476   0.5968
   8.500   0.9459   0.01884   0.01126  -0.0626   0.1345   0.6028
   8.750   0.9615   0.01947   0.01186  -0.0610   0.1222   0.6081
   9.000   0.9766   0.02012   0.01249  -0.0593   0.1111   0.6142
   9.250   0.9914   0.02081   0.01315  -0.0577   0.1005   0.6204
   9.500   1.0062   0.02153   0.01383  -0.0561   0.0908   0.6266
   9.750   1.0206   0.02226   0.01456  -0.0545   0.0820   0.6320
  10.000   1.0350   0.02302   0.01531  -0.0530   0.0739   0.6381
  10.250   1.0492   0.02381   0.01609  -0.0515   0.0668   0.6446
  10.750   1.0770   0.02547   0.01776  -0.0485   0.0549   0.6564
  11.000   1.0904   0.02636   0.01866  -0.0471   0.0502   0.6627
  11.250   1.1042   0.02726   0.01957  -0.0457   0.0457   0.6692
  11.500   1.1177   0.02818   0.02051  -0.0444   0.0423   0.6752
  11.750   1.1305   0.02916   0.02153  -0.0431   0.0391   0.6814
  12.000   1.1432   0.03019   0.02258  -0.0418   0.0362   0.6878
  12.250   1.1558   0.03125   0.02367  -0.0405   0.0336   0.6941
  12.500   1.1679   0.03235   0.02482  -0.0393   0.0315   0.7004
  12.750   1.1797   0.03350   0.02603  -0.0381   0.0295   0.7072
  13.000   1.1913   0.03472   0.02727  -0.0370   0.0278   0.7137
  13.250   1.2026   0.03596   0.02857  -0.0359   0.0262   0.7198
  13.500   1.2131   0.03729   0.02996  -0.0348   0.0249   0.7269
  13.750   1.2239   0.03865   0.03138  -0.0339   0.0237   0.7339
  14.000   1.2341   0.04008   0.03286  -0.0329   0.0226   0.7401
  14.250   1.2431   0.04163   0.03448  -0.0320   0.0217   0.7470
  14.500   1.2525   0.04321   0.03612  -0.0312   0.0209   0.7543
  14.750   1.2615   0.04484   0.03783  -0.0304   0.0200   0.7612
  15.000   1.2697   0.04658   0.03965  -0.0297   0.0193   0.7686
  15.250   1.2766   0.04851   0.04164  -0.0290   0.0186   0.7758
  15.500   1.2840   0.05040   0.04361  -0.0285   0.0179   0.7828
  15.750   1.2908   0.05241   0.04571  -0.0280   0.0173   0.7910
  16.000   1.2973   0.05451   0.04789  -0.0276   0.0168   0.7986
  16.250   1.3022   0.05680   0.05027  -0.0273   0.0163   0.8065
  16.500   1.3066   0.05923   0.05278  -0.0271   0.0158   0.8150
  16.750   1.3101   0.06176   0.05540  -0.0269   0.0154   0.8230
  17.000   1.3139   0.06435   0.05810  -0.0269   0.0150   0.8327
  17.250   1.3171   0.06703   0.06089  -0.0270   0.0147   0.8422
  17.500   1.3194   0.06990   0.06386  -0.0272   0.0143   0.8526
  17.750   1.3203   0.07293   0.06701  -0.0275   0.0140   0.8644
  18.000   1.3203   0.07607   0.07027  -0.0278   0.0137   0.8793
  18.250   1.3185   0.07934   0.07368  -0.0281   0.0135   0.9066
  18.500   1.3154   0.08292   0.07739  -0.0289   0.0131   1.0000
  18.750   1.3124   0.08701   0.08157  -0.0303   0.0130   1.0000
<< Back to NREL's S835 Airfoil (s835-nr)

Polar data table (+)

Polar graphs


<< Back to NREL's S835 Airfoil (s835-nr)