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NREL's S803 Airfoil (s803-nr) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NREL's S803 Airfoil (s803-nr)
Reynolds number: 200,000
Max Cl/Cd: 89.49 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s803-nr-200000.txt
Download as CSV file: xf-s803-nr-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S803 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3587   0.10496   0.10146  -0.0434   1.0000   0.0501
  -9.250  -0.3733   0.10188   0.09847  -0.0460   1.0000   0.0506
  -9.000  -0.3837   0.09886   0.09552  -0.0468   1.0000   0.0508
  -8.750  -0.3853   0.09410   0.09082  -0.0446   1.0000   0.0517
  -8.500  -0.3777   0.09230   0.08904  -0.0414   1.0000   0.0528
  -8.250  -0.3757   0.09094   0.08772  -0.0387   1.0000   0.0544
  -8.000  -0.3844   0.08928   0.08613  -0.0365   1.0000   0.0558
  -7.750  -0.4009   0.08771   0.08466  -0.0339   1.0000   0.0562
  -7.500  -0.3938   0.08318   0.08015  -0.0405   0.9951   0.0596
  -7.250  -0.3782   0.06807   0.06454  -0.0781   0.9752   0.0627
  -7.000  -0.3592   0.06335   0.06015  -0.0753   0.9741   0.0649
  -6.750  -0.3361   0.06036   0.05713  -0.0777   0.9673   0.0672
  -6.250  -0.2846   0.04722   0.04337  -0.0960   0.9509   0.0785
  -6.000  -0.2499   0.04402   0.04010  -0.1000   0.9480   0.0828
  -5.750  -0.2124   0.03185   0.02612  -0.1073   0.9383   0.0512
  -5.500  -0.1754   0.02673   0.02074  -0.1109   0.9357   0.0474
  -5.250  -0.1394   0.02315   0.01656  -0.1130   0.9303   0.0445
  -5.000  -0.1024   0.02099   0.01401  -0.1148   0.9252   0.0442
  -4.750  -0.0620   0.01947   0.01233  -0.1173   0.9223   0.0458
  -4.500  -0.0196   0.01821   0.01092  -0.1200   0.9202   0.0484
  -4.250   0.0126   0.01713   0.00972  -0.1207   0.9120   0.0497
  -4.000   0.0537   0.01579   0.00834  -0.1233   0.9082   0.0520
  -3.750   0.0973   0.01467   0.00727  -0.1266   0.9051   0.0577
  -3.500   0.1303   0.01390   0.00650  -0.1278   0.8955   0.0669
  -3.250   0.1745   0.01236   0.00543  -0.1318   0.8909   0.1654
  -3.000   0.2088   0.01124   0.00507  -0.1341   0.8813   0.3637
  -2.750   0.2452   0.01064   0.00523  -0.1357   0.8748   0.5884
  -2.500   0.2733   0.01086   0.00546  -0.1351   0.8637   0.6549
  -2.250   0.3022   0.01109   0.00563  -0.1346   0.8541   0.6900
  -2.000   0.3317   0.01126   0.00573  -0.1342   0.8457   0.7123
  -1.750   0.3562   0.01147   0.00589  -0.1329   0.8354   0.7312
  -1.500   0.3836   0.01162   0.00596  -0.1322   0.8272   0.7471
  -1.250   0.4088   0.01175   0.00602  -0.1312   0.8179   0.7605
  -1.000   0.4346   0.01188   0.00608  -0.1304   0.8097   0.7733
  -0.750   0.4616   0.01198   0.00610  -0.1300   0.8019   0.7852
  -0.500   0.4858   0.01208   0.00617  -0.1289   0.7943   0.7953
  -0.250   0.5111   0.01216   0.00620  -0.1280   0.7868   0.8052
   0.000   0.5378   0.01226   0.00625  -0.1277   0.7801   0.8156
   0.250   0.5615   0.01233   0.00630  -0.1266   0.7730   0.8246
   0.500   0.5886   0.01240   0.00631  -0.1263   0.7673   0.8334
   0.750   0.6130   0.01248   0.00640  -0.1256   0.7599   0.8416
   1.000   0.6409   0.01253   0.00640  -0.1255   0.7544   0.8480
   1.250   0.6660   0.01261   0.00650  -0.1250   0.7478   0.8545
   1.500   0.6941   0.01268   0.00654  -0.1252   0.7415   0.8606
   1.750   0.7209   0.01274   0.00658  -0.1249   0.7358   0.8661
   2.000   0.7473   0.01283   0.00670  -0.1248   0.7286   0.8723
   2.250   0.7758   0.01286   0.00669  -0.1248   0.7228   0.8774
   2.500   0.7998   0.01293   0.00682  -0.1241   0.7148   0.8836
   2.750   0.8289   0.01297   0.00683  -0.1244   0.7080   0.8895
   3.000   0.8519   0.01300   0.00692  -0.1234   0.6994   0.8959
   3.250   0.8812   0.01301   0.00688  -0.1236   0.6918   0.9029
   3.500   0.9025   0.01299   0.00694  -0.1222   0.6818   0.9107
   3.750   0.9287   0.01298   0.00695  -0.1217   0.6729   0.9188
   4.000   0.9530   0.01293   0.00693  -0.1209   0.6633   0.9292
   4.250   0.9754   0.01288   0.00695  -0.1196   0.6533   0.9429
   4.500   1.0039   0.01281   0.00690  -0.1197   0.6429   0.9631
   4.750   1.0369   0.01283   0.00695  -0.1209   0.6312   1.0000
   5.000   1.0664   0.01293   0.00710  -0.1214   0.6186   1.0000
   5.250   1.0955   0.01302   0.00723  -0.1219   0.6050   1.0000
   5.500   1.1238   0.01311   0.00736  -0.1221   0.5901   1.0000
   5.750   1.1508   0.01321   0.00748  -0.1221   0.5736   1.0000
   6.000   1.1766   0.01332   0.00757  -0.1217   0.5543   1.0000
   6.250   1.2000   0.01346   0.00777  -0.1209   0.5301   1.0000
   6.500   1.2216   0.01365   0.00794  -0.1197   0.4992   1.0000
   6.750   1.2397   0.01400   0.00815  -0.1179   0.4523   1.0000
   7.000   1.2502   0.01479   0.00855  -0.1148   0.3825   1.0000
   7.250   1.2563   0.01600   0.00932  -0.1113   0.3149   1.0000
   7.500   1.2626   0.01727   0.01024  -0.1080   0.2571   1.0000
   7.750   1.2687   0.01852   0.01119  -0.1046   0.2118   1.0000
   8.000   1.2749   0.01969   0.01216  -0.1014   0.1783   1.0000
   8.250   1.2813   0.02090   0.01319  -0.0982   0.1540   1.0000
   8.500   1.2893   0.02205   0.01426  -0.0954   0.1358   1.0000
   8.750   1.2971   0.02325   0.01539  -0.0926   0.1219   1.0000
   9.250   1.3148   0.02565   0.01777  -0.0878   0.1019   1.0000
   9.500   1.3224   0.02706   0.01918  -0.0853   0.0949   1.0000
   9.750   1.3327   0.02828   0.02043  -0.0834   0.0885   1.0000
  10.000   1.3408   0.02985   0.02200  -0.0813   0.0831   1.0000
  10.250   1.3525   0.03108   0.02332  -0.0796   0.0781   1.0000
  10.500   1.3621   0.03269   0.02490  -0.0779   0.0739   1.0000
  10.750   1.3749   0.03420   0.02650  -0.0765   0.0702   1.0000
  11.000   1.3871   0.03554   0.02796  -0.0751   0.0665   1.0000
  11.250   1.3988   0.03704   0.02947  -0.0738   0.0633   1.0000
  11.500   1.4165   0.03890   0.03134  -0.0729   0.0600   1.0000
  11.750   1.4278   0.04037   0.03300  -0.0716   0.0574   1.0000
  12.000   1.4387   0.04193   0.03469  -0.0703   0.0548   1.0000
  12.250   1.4508   0.04357   0.03636  -0.0693   0.0524   1.0000
  12.500   1.4694   0.04586   0.03874  -0.0687   0.0496   1.0000
  12.750   1.4749   0.04771   0.04082  -0.0672   0.0478   1.0000
  13.000   1.4810   0.04969   0.04298  -0.0660   0.0457   1.0000
  13.250   1.4864   0.05165   0.04503  -0.0650   0.0438   1.0000
  13.500   1.4983   0.05395   0.04730  -0.0644   0.0413   1.0000
  13.750   1.4980   0.05687   0.05052  -0.0632   0.0399   1.0000
  14.000   1.4959   0.05963   0.05353  -0.0622   0.0384   1.0000
  14.250   1.4946   0.06244   0.05653  -0.0615   0.0369   1.0000
  14.500   1.4937   0.06518   0.05939  -0.0611   0.0354   1.0000
  14.750   1.4966   0.06775   0.06198  -0.0609   0.0340   1.0000
  15.000   1.4932   0.07222   0.06663  -0.0606   0.0326   1.0000
  15.250   1.4814   0.07646   0.07118  -0.0608   0.0319   1.0000
  15.500   1.4691   0.08118   0.07617  -0.0614   0.0311   1.0000
  15.750   1.4572   0.08608   0.08133  -0.0625   0.0302   1.0000
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