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USA 35 A AIRFOIL (usa35a-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: USA 35 A AIRFOIL (usa35a-il)
Reynolds number: 500,000
Max Cl/Cd: 97.8 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa35a-il-500000.txt
Download as CSV file: xf-usa35a-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 35 A 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.0107   0.09652   0.09346  -0.0856   0.8274   0.0466
  -9.750  -0.2085   0.04642   0.04309  -0.1259   0.8229   0.0416
  -9.500  -0.2519   0.03615   0.03227  -0.1342   0.8116   0.0412
  -9.250  -0.2731   0.02848   0.02375  -0.1357   0.8015   0.0412
  -9.000  -0.2625   0.02562   0.02037  -0.1354   0.7931   0.0415
  -8.750  -0.2451   0.02357   0.01809  -0.1351   0.7841   0.0419
  -8.500  -0.2223   0.02260   0.01699  -0.1347   0.7754   0.0422
  -8.250  -0.1979   0.02187   0.01619  -0.1345   0.7665   0.0426
  -8.000  -0.1735   0.02118   0.01539  -0.1341   0.7569   0.0430
  -7.750  -0.1485   0.02050   0.01460  -0.1338   0.7475   0.0434
  -7.500  -0.1238   0.01974   0.01369  -0.1335   0.7371   0.0440
  -7.250  -0.0990   0.01895   0.01270  -0.1331   0.7268   0.0446
  -7.000  -0.0739   0.01824   0.01177  -0.1327   0.7150   0.0454
  -6.750  -0.0481   0.01766   0.01096  -0.1323   0.7029   0.0461
  -6.250   0.0036   0.01657   0.00976  -0.1317   0.6764   0.0474
  -6.000   0.0301   0.01624   0.00932  -0.1314   0.6634   0.0481
  -5.750   0.0564   0.01590   0.00885  -0.1310   0.6503   0.0489
  -5.500   0.0833   0.01552   0.00835  -0.1307   0.6383   0.0499
  -5.250   0.1100   0.01528   0.00790  -0.1303   0.6272   0.0507
  -5.000   0.1366   0.01477   0.00739  -0.1301   0.6171   0.0517
  -4.500   0.1912   0.01439   0.00689  -0.1297   0.5995   0.0540
  -4.250   0.2185   0.01425   0.00662  -0.1294   0.5910   0.0555
  -4.000   0.2455   0.01394   0.00630  -0.1292   0.5833   0.0570
  -3.750   0.2731   0.01381   0.00615  -0.1290   0.5759   0.0585
  -3.500   0.3006   0.01371   0.00594  -0.1288   0.5695   0.0604
  -3.250   0.3282   0.01347   0.00567  -0.1286   0.5646   0.0622
  -3.000   0.3563   0.01331   0.00555  -0.1286   0.5600   0.0641
  -2.750   0.3844   0.01323   0.00540  -0.1285   0.5551   0.0664
  -2.500   0.4119   0.01307   0.00522  -0.1283   0.5505   0.0688
  -2.250   0.4399   0.01306   0.00517  -0.1283   0.5460   0.0716
  -2.000   0.4682   0.01290   0.00502  -0.1282   0.5427   0.0745
  -1.750   0.4963   0.01278   0.00494  -0.1282   0.5390   0.0774
  -1.500   0.5246   0.01273   0.00485  -0.1281   0.5351   0.0806
  -1.250   0.5522   0.01262   0.00475  -0.1280   0.5310   0.0844
  -1.000   0.5803   0.01267   0.00473  -0.1280   0.5265   0.0882
  -0.750   0.6083   0.01253   0.00465  -0.1280   0.5235   0.0928
  -0.500   0.6365   0.01244   0.00458  -0.1280   0.5202   0.0980
  -0.250   0.6646   0.01237   0.00454  -0.1279   0.5167   0.1043
   0.000   0.6925   0.01230   0.00450  -0.1279   0.5131   0.1127
   0.250   0.7202   0.01226   0.00448  -0.1278   0.5093   0.1260
   0.500   0.7481   0.01218   0.00456  -0.1279   0.5052   0.1786
   0.750   0.7755   0.01198   0.00461  -0.1279   0.5020   0.2469
   1.000   0.8027   0.01175   0.00467  -0.1279   0.4982   0.3360
   1.250   0.8294   0.01150   0.00478  -0.1278   0.4943   0.4702
   1.500   0.8554   0.01125   0.00488  -0.1276   0.4905   0.5925
   1.750   0.8766   0.01091   0.00510  -0.1261   0.4863   0.8081
   2.000   0.9113   0.01072   0.00520  -0.1269   0.4828   1.0000
   2.250   0.9378   0.01080   0.00525  -0.1266   0.4788   1.0000
   2.500   0.9641   0.01090   0.00531  -0.1262   0.4746   1.0000
   2.750   0.9902   0.01104   0.00538  -0.1259   0.4702   1.0000
   3.000   1.0163   0.01125   0.00549  -0.1255   0.4654   1.0000
   3.250   1.0421   0.01132   0.00557  -0.1251   0.4609   1.0000
   3.500   1.0675   0.01142   0.00564  -0.1247   0.4553   1.0000
   3.750   1.0919   0.01159   0.00573  -0.1240   0.4494   1.0000
   4.000   1.1168   0.01173   0.00585  -0.1235   0.4437   1.0000
   4.250   1.1417   0.01185   0.00596  -0.1229   0.4374   1.0000
   4.500   1.1649   0.01204   0.00608  -0.1221   0.4311   1.0000
   4.750   1.1887   0.01221   0.00623  -0.1214   0.4246   1.0000
   5.000   1.2118   0.01239   0.00638  -0.1206   0.4173   1.0000
   5.250   1.2320   0.01266   0.00657  -0.1193   0.4103   1.0000
   5.500   1.2539   0.01283   0.00675  -0.1182   0.4031   1.0000
   5.750   1.2727   0.01312   0.00697  -0.1167   0.3955   1.0000
   6.000   1.2931   0.01340   0.00723  -0.1155   0.3885   1.0000
   6.250   1.3129   0.01371   0.00750  -0.1142   0.3814   1.0000
   6.500   1.3311   0.01412   0.00785  -0.1127   0.3750   1.0000
   6.750   1.3523   0.01442   0.00816  -0.1118   0.3689   1.0000
   7.000   1.3706   0.01484   0.00853  -0.1104   0.3624   1.0000
   7.250   1.3888   0.01530   0.00895  -0.1091   0.3568   1.0000
   7.500   1.4093   0.01567   0.00932  -0.1082   0.3518   1.0000
   7.750   1.4278   0.01613   0.00976  -0.1069   0.3469   1.0000
   8.000   1.4444   0.01670   0.01028  -0.1055   0.3423   1.0000
   8.250   1.4644   0.01712   0.01073  -0.1046   0.3386   1.0000
   8.500   1.4837   0.01758   0.01120  -0.1036   0.3346   1.0000
   8.750   1.5015   0.01811   0.01173  -0.1025   0.3306   1.0000
   9.000   1.5171   0.01877   0.01236  -0.1011   0.3267   1.0000
   9.250   1.5345   0.01937   0.01296  -0.1000   0.3231   1.0000
   9.500   1.5533   0.01988   0.01352  -0.0991   0.3197   1.0000
   9.750   1.5701   0.02051   0.01416  -0.0980   0.3159   1.0000
  10.000   1.5852   0.02125   0.01490  -0.0968   0.3121   1.0000
  10.250   1.5982   0.02213   0.01574  -0.0953   0.3080   1.0000
  10.500   1.6160   0.02275   0.01643  -0.0945   0.3051   1.0000
  10.750   1.6323   0.02346   0.01719  -0.0936   0.3017   1.0000
  11.000   1.6468   0.02430   0.01805  -0.0925   0.2980   1.0000
  11.250   1.6587   0.02532   0.01906  -0.0911   0.2943   1.0000
  11.500   1.6712   0.02631   0.02006  -0.0899   0.2907   1.0000
  11.750   1.6861   0.02718   0.02101  -0.0891   0.2873   1.0000
  12.000   1.6993   0.02817   0.02205  -0.0881   0.2833   1.0000
  12.250   1.7091   0.02942   0.02331  -0.0869   0.2793   1.0000
  12.500   1.7174   0.03079   0.02467  -0.0856   0.2751   1.0000
  12.750   1.7304   0.03191   0.02589  -0.0848   0.2711   1.0000
  13.000   1.7400   0.03328   0.02730  -0.0838   0.2662   1.0000
  13.250   1.7445   0.03509   0.02910  -0.0825   0.2613   1.0000
  13.500   1.7538   0.03659   0.03067  -0.0817   0.2565   1.0000
  13.750   1.7606   0.03833   0.03245  -0.0808   0.2507   1.0000
  14.000   1.7601   0.04073   0.03483  -0.0796   0.2449   1.0000
  14.250   1.7668   0.04260   0.03678  -0.0789   0.2385   1.0000
  14.500   1.7639   0.04537   0.03954  -0.0778   0.2317   1.0000
  14.750   1.7665   0.04770   0.04193  -0.0771   0.2249   1.0000
  15.000   1.7611   0.05086   0.04508  -0.0761   0.2182   1.0000
  15.250   1.7601   0.05362   0.04789  -0.0755   0.2121   1.0000
  15.500   1.7554   0.05681   0.05110  -0.0747   0.2064   1.0000
  15.750   1.7513   0.05997   0.05427  -0.0741   0.2016   1.0000
  16.000   1.7499   0.06288   0.05723  -0.0736   0.1971   1.0000
  16.250   1.7440   0.06628   0.06063  -0.0731   0.1929   1.0000
  16.500   1.7404   0.06943   0.06380  -0.0727   0.1893   1.0000
  16.750   1.7408   0.07222   0.06667  -0.0724   0.1861   1.0000
  17.000   1.7399   0.07512   0.06960  -0.0722   0.1831   1.0000
  17.250   1.7359   0.07836   0.07286  -0.0719   0.1804   1.0000
  17.500   1.7345   0.08123   0.07572  -0.0717   0.1775   1.0000
  17.750   1.7362   0.08393   0.07851  -0.0716   0.1756   1.0000
  18.000   1.7380   0.08658   0.08123  -0.0716   0.1734   1.0000
  18.250   1.7390   0.08930   0.08400  -0.0716   0.1712   1.0000
  18.500   1.7381   0.09224   0.08696  -0.0717   0.1691   1.0000
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