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 S804 Airfoil (s804-nr) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NREL's S804 Airfoil (s804-nr)
Reynolds number: 200,000
Max Cl/Cd: 58.23 at α=11.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s804-nr-200000.txt
Download as CSV file: xf-s804-nr-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S804 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5127   0.06327   0.05946  -0.0742   1.0000   0.0464
 -10.250  -0.5363   0.06117   0.05741  -0.0718   1.0000   0.0463
 -10.000  -0.5344   0.05464   0.05068  -0.0817   0.9893   0.0460
  -9.750  -0.5223   0.04801   0.04373  -0.0919   0.9745   0.0453
  -9.500  -0.5099   0.04172   0.03695  -0.0992   0.9594   0.0445
  -9.250  -0.4902   0.03685   0.03156  -0.1038   0.9459   0.0443
  -9.000  -0.4640   0.03324   0.02753  -0.1070   0.9334   0.0446
  -8.750  -0.4318   0.03021   0.02406  -0.1101   0.9225   0.0454
  -8.500  -0.3902   0.02763   0.02096  -0.1145   0.9135   0.0468
  -8.250  -0.3493   0.02605   0.01947  -0.1174   0.9002   0.0487
  -8.000  -0.3063   0.02444   0.01766  -0.1208   0.8841   0.0506
  -7.750  -0.2637   0.02297   0.01580  -0.1240   0.8644   0.0523
  -7.500  -0.2246   0.02159   0.01445  -0.1263   0.8435   0.0544
  -7.250  -0.1910   0.02082   0.01348  -0.1275   0.8217   0.0571
  -7.000  -0.1645   0.02004   0.01257  -0.1273   0.7998   0.0596
  -6.750  -0.1395   0.01943   0.01192  -0.1268   0.7793   0.0621
  -6.500  -0.1145   0.01892   0.01122  -0.1263   0.7607   0.0650
  -6.250  -0.0913   0.01827   0.01057  -0.1257   0.7430   0.0685
  -6.000  -0.0668   0.01783   0.01002  -0.1252   0.7263   0.0730
  -5.750  -0.0428   0.01720   0.00940  -0.1249   0.7111   0.0779
  -5.500  -0.0174   0.01665   0.00878  -0.1248   0.6971   0.0854
  -5.250   0.0081   0.01606   0.00819  -0.1248   0.6826   0.0981
  -5.000   0.0346   0.01524   0.00749  -0.1253   0.6689   0.1287
  -4.750   0.0625   0.01430   0.00684  -0.1265   0.6567   0.2040
  -4.500   0.0904   0.01356   0.00646  -0.1274   0.6436   0.2965
  -4.250   0.1187   0.01336   0.00650  -0.1277   0.6323   0.3801
  -4.000   0.1470   0.01350   0.00661  -0.1276   0.6209   0.4255
  -3.750   0.1754   0.01373   0.00673  -0.1274   0.6102   0.4538
  -3.500   0.2032   0.01401   0.00692  -0.1270   0.5999   0.4761
  -3.250   0.2306   0.01437   0.00722  -0.1264   0.5900   0.4968
  -3.000   0.2582   0.01470   0.00742  -0.1260   0.5803   0.5144
  -2.750   0.2846   0.01498   0.00768  -0.1251   0.5714   0.5253
  -2.500   0.3125   0.01515   0.00774  -0.1249   0.5623   0.5372
  -2.250   0.3394   0.01546   0.00796  -0.1242   0.5548   0.5470
  -2.000   0.3674   0.01558   0.00802  -0.1241   0.5465   0.5578
  -1.750   0.3937   0.01578   0.00818  -0.1233   0.5394   0.5654
  -1.500   0.4226   0.01599   0.00825  -0.1234   0.5327   0.5752
  -1.250   0.4493   0.01606   0.00833  -0.1229   0.5257   0.5820
  -1.000   0.4766   0.01623   0.00843  -0.1225   0.5196   0.5892
  -0.750   0.5064   0.01642   0.00846  -0.1230   0.5138   0.5976
  -0.500   0.5327   0.01646   0.00854  -0.1225   0.5075   0.6029
  -0.250   0.5601   0.01657   0.00860  -0.1222   0.5018   0.6088
   0.000   0.5899   0.01677   0.00863  -0.1226   0.4968   0.6155
   0.250   0.6182   0.01684   0.00869  -0.1227   0.4918   0.6211
   0.500   0.6451   0.01692   0.00880  -0.1224   0.4869   0.6255
   0.750   0.6733   0.01704   0.00887  -0.1224   0.4824   0.6308
   1.000   0.7033   0.01722   0.00892  -0.1229   0.4785   0.6366
   1.250   0.7325   0.01741   0.00906  -0.1233   0.4746   0.6414
   1.500   0.7589   0.01751   0.00923  -0.1230   0.4705   0.6457
   1.750   0.7866   0.01765   0.00937  -0.1230   0.4663   0.6507
   2.000   0.8158   0.01779   0.00944  -0.1233   0.4626   0.6561
   2.250   0.8458   0.01800   0.00955  -0.1238   0.4593   0.6614
   2.500   0.8732   0.01828   0.00985  -0.1237   0.4562   0.6661
   2.750   0.8997   0.01847   0.01012  -0.1235   0.4530   0.6717
   3.000   0.9278   0.01868   0.01035  -0.1237   0.4497   0.6778
   3.250   0.9558   0.01888   0.01056  -0.1239   0.4467   0.6831
   3.500   0.9832   0.01909   0.01079  -0.1238   0.4439   0.6884
   3.750   1.0120   0.01935   0.01101  -0.1241   0.4413   0.6954
   4.000   1.0419   0.01980   0.01138  -0.1246   0.4385   0.7024
   4.250   1.0663   0.02002   0.01175  -0.1241   0.4359   0.7085
   4.500   1.0923   0.02032   0.01214  -0.1239   0.4332   0.7160
   4.750   1.1187   0.02062   0.01252  -0.1238   0.4306   0.7232
   5.000   1.1446   0.02092   0.01290  -0.1235   0.4281   0.7307
   5.250   1.1723   0.02125   0.01323  -0.1237   0.4258   0.7403
   5.500   1.1988   0.02152   0.01355  -0.1235   0.4235   0.7487
   5.750   1.2280   0.02192   0.01391  -0.1239   0.4211   0.7594
   6.000   1.2531   0.02244   0.01451  -0.1236   0.4189   0.7685
   6.250   1.2764   0.02284   0.01508  -0.1230   0.4168   0.7799
   6.500   1.2987   0.02325   0.01563  -0.1222   0.4143   0.7917
   6.750   1.3212   0.02361   0.01613  -0.1214   0.4116   0.8047
   7.000   1.3442   0.02395   0.01659  -0.1207   0.4090   0.8196
   7.250   1.3675   0.02426   0.01698  -0.1199   0.4067   0.8359
   7.500   1.3916   0.02454   0.01729  -0.1193   0.4045   0.8544
   7.750   1.4177   0.02494   0.01769  -0.1190   0.4023   0.8786
   8.000   1.4357   0.02540   0.01830  -0.1175   0.4000   0.9112
   8.250   1.4535   0.02575   0.01887  -0.1161   0.3971   1.0000
   8.500   1.4788   0.02635   0.01955  -0.1164   0.3939   1.0000
   8.750   1.5047   0.02679   0.02004  -0.1166   0.3906   1.0000
   9.000   1.5327   0.02708   0.02031  -0.1170   0.3877   1.0000
   9.250   1.5647   0.02732   0.02047  -0.1179   0.3848   1.0000
   9.500   1.5889   0.02798   0.02117  -0.1177   0.3816   1.0000
   9.750   1.6037   0.02859   0.02196  -0.1161   0.3778   1.0000
  10.000   1.6229   0.02902   0.02249  -0.1151   0.3739   1.0000
  10.250   1.6480   0.02915   0.02262  -0.1148   0.3703   1.0000
  10.500   1.6814   0.02910   0.02245  -0.1157   0.3668   1.0000
  10.750   1.7000   0.02969   0.02314  -0.1146   0.3630   1.0000
  11.000   1.7090   0.03031   0.02395  -0.1121   0.3588   1.0000
  11.250   1.7263   0.03058   0.02430  -0.1107   0.3546   1.0000
  11.500   1.7551   0.03045   0.02412  -0.1109   0.3508   1.0000
  11.750   1.7842   0.03064   0.02425  -0.1112   0.3469   1.0000
  12.000   1.7807   0.03147   0.02533  -0.1070   0.3426   1.0000
  12.250   1.7876   0.03188   0.02585  -0.1040   0.3382   1.0000
  12.500   1.8106   0.03173   0.02567  -0.1033   0.3340   1.0000
  12.750   1.8320   0.03188   0.02579  -0.1024   0.3297   1.0000
  13.000   1.8151   0.03302   0.02717  -0.0966   0.3255   1.0000
  13.250   1.8158   0.03368   0.02793  -0.0934   0.3207   1.0000
  13.500   1.8362   0.03359   0.02779  -0.0924   0.3160   1.0000
  13.750   1.8315   0.03479   0.02912  -0.0891   0.3114   1.0000
  14.000   1.8170   0.03659   0.03111  -0.0854   0.3062   1.0000
  14.250   1.8232   0.03736   0.03191  -0.0837   0.3009   1.0000
  14.500   1.8208   0.03892   0.03354  -0.0817   0.2955   1.0000
  14.750   1.8011   0.04193   0.03676  -0.0793   0.2893   1.0000
  15.000   1.8105   0.04283   0.03761  -0.0784   0.2831   1.0000
  15.250   1.7803   0.04753   0.04256  -0.0769   0.2759   1.0000
  15.500   1.7780   0.04984   0.04488  -0.0763   0.2686   1.0000
  15.750   1.7483   0.05548   0.05071  -0.0762   0.2600   1.0000
  16.000   1.7417   0.05875   0.05397  -0.0762   0.2513   1.0000
  16.250   1.7171   0.06454   0.05986  -0.0770   0.2412   1.0000
  16.500   1.6950   0.07036   0.06574  -0.0780   0.2308   1.0000
  16.750   1.6806   0.07530   0.07066  -0.0789   0.2205   1.0000
  17.000   1.6713   0.07958   0.07484  -0.0797   0.2100   1.0000
  17.250   1.6504   0.08582   0.08112  -0.0814   0.1995   1.0000
  17.500   1.6356   0.09127   0.08658  -0.0828   0.1897   1.0000
<< Back to NREL's S804 Airfoil (s804-nr)

Polar data table (+)

Polar graphs


<< Back to NREL's S804 Airfoil (s804-nr)