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USA 98 AIRFOIL (usa98-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: USA 98 AIRFOIL (usa98-il)
Reynolds number: 500,000
Max Cl/Cd: 120.34 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa98-il-500000.txt
Download as CSV file: xf-usa98-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 98 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.0843   0.09823   0.09555  -0.0854   0.9743   0.0496
  -8.750  -0.0639   0.09470   0.09201  -0.0899   0.9711   0.0505
  -8.250  -0.0592   0.08358   0.08086  -0.1021   0.9490   0.0535
  -8.000  -0.0387   0.08114   0.07841  -0.1037   0.9351   0.0537
  -7.750  -0.0124   0.07837   0.07561  -0.1071   0.9166   0.0540
  -7.500   0.0154   0.07536   0.07249  -0.1114   0.8889   0.0545
  -7.250   0.0315   0.07290   0.06982  -0.1135   0.8562   0.0551
  -7.000   0.0126   0.06179   0.05848  -0.1310   0.8294   0.0591
  -6.750   0.0272   0.06049   0.05713  -0.1297   0.8186   0.0594
  -6.500   0.0435   0.05916   0.05573  -0.1296   0.8090   0.0596
  -6.250   0.0608   0.05771   0.05424  -0.1302   0.8009   0.0600
  -6.000   0.0892   0.03811   0.03411  -0.1667   0.7922   0.0661
  -5.750   0.1119   0.03683   0.03280  -0.1670   0.7856   0.0664
  -5.500   0.1355   0.03553   0.03151  -0.1677   0.7794   0.0669
  -5.250   0.1606   0.03400   0.02992  -0.1693   0.7729   0.0675
  -5.000   0.1879   0.03204   0.02780  -0.1719   0.7669   0.0686
  -4.750   0.2235   0.02692   0.02201  -0.1799   0.7616   0.0740
  -4.500   0.2607   0.01961   0.01346  -0.1852   0.7565   0.0592
  -4.250   0.2899   0.01879   0.01249  -0.1858   0.7507   0.0590
  -4.000   0.3195   0.01778   0.01128  -0.1864   0.7451   0.0590
  -3.750   0.3488   0.01674   0.01011  -0.1870   0.7399   0.0591
  -3.500   0.3779   0.01561   0.00889  -0.1876   0.7343   0.0595
  -3.250   0.4069   0.01499   0.00822  -0.1879   0.7287   0.0603
  -3.000   0.4360   0.01462   0.00781  -0.1882   0.7232   0.0610
  -2.750   0.4651   0.01418   0.00734  -0.1884   0.7177   0.0615
  -2.500   0.4942   0.01379   0.00689  -0.1886   0.7120   0.0620
  -2.250   0.5235   0.01348   0.00649  -0.1888   0.7064   0.0626
  -2.000   0.5526   0.01314   0.00614  -0.1889   0.7008   0.0633
  -1.750   0.5816   0.01285   0.00582  -0.1890   0.6949   0.0640
  -1.500   0.6107   0.01264   0.00554  -0.1891   0.6892   0.0647
  -1.250   0.6398   0.01250   0.00534  -0.1892   0.6834   0.0654
  -1.000   0.6687   0.01207   0.00495  -0.1894   0.6773   0.0667
  -0.750   0.6976   0.01188   0.00477  -0.1895   0.6713   0.0681
  -0.500   0.7267   0.01179   0.00464  -0.1897   0.6655   0.0694
  -0.250   0.7554   0.01163   0.00451  -0.1897   0.6592   0.0707
   0.000   0.7842   0.01153   0.00438  -0.1897   0.6528   0.0721
   0.250   0.8132   0.01145   0.00424  -0.1898   0.6468   0.0736
   0.500   0.8420   0.01128   0.00413  -0.1899   0.6405   0.0759
   0.750   0.8705   0.01123   0.00407  -0.1899   0.6339   0.0786
   1.000   0.8991   0.01124   0.00402  -0.1899   0.6277   0.0819
   1.250   0.9277   0.01113   0.00398  -0.1900   0.6213   0.0867
   1.500   0.9561   0.01108   0.00393  -0.1899   0.6146   0.0943
   1.750   0.9854   0.01072   0.00395  -0.1904   0.6083   0.2492
   2.000   1.0133   0.01060   0.00410  -0.1904   0.6010   0.3499
   2.250   1.0404   0.01067   0.00419  -0.1901   0.5928   0.3842
   2.500   1.0674   0.01074   0.00429  -0.1898   0.5842   0.4075
   2.750   1.0942   0.01082   0.00437  -0.1894   0.5758   0.4280
   3.000   1.1213   0.01093   0.00449  -0.1891   0.5690   0.4477
   3.250   1.1485   0.01099   0.00462  -0.1889   0.5619   0.4687
   3.500   1.1751   0.01111   0.00474  -0.1885   0.5551   0.4900
   3.750   1.2021   0.01118   0.00488  -0.1883   0.5489   0.5131
   4.000   1.2289   0.01124   0.00502  -0.1880   0.5420   0.5429
   4.250   1.2549   0.01132   0.00518  -0.1875   0.5351   0.5880
   4.500   1.2808   0.01114   0.00540  -0.1871   0.5287   0.7347
   4.750   1.3011   0.01087   0.00545  -0.1852   0.5222   1.0000
   5.000   1.3265   0.01111   0.00560  -0.1846   0.5152   1.0000
   5.250   1.3523   0.01124   0.00575  -0.1841   0.5069   1.0000
   5.500   1.3766   0.01149   0.00591  -0.1833   0.4983   1.0000
   5.750   1.4019   0.01165   0.00608  -0.1827   0.4901   1.0000
   6.000   1.4257   0.01188   0.00626  -0.1818   0.4815   1.0000
   6.250   1.4501   0.01208   0.00647  -0.1810   0.4736   1.0000
   6.500   1.4735   0.01231   0.00667  -0.1801   0.4647   1.0000
   6.750   1.4963   0.01255   0.00689  -0.1790   0.4552   1.0000
   7.000   1.5177   0.01283   0.00713  -0.1777   0.4446   1.0000
   7.250   1.5400   0.01308   0.00738  -0.1765   0.4350   1.0000
   7.500   1.5592   0.01343   0.00767  -0.1748   0.4243   1.0000
   7.750   1.5796   0.01371   0.00795  -0.1733   0.4117   1.0000
   8.000   1.5973   0.01407   0.00828  -0.1713   0.3986   1.0000
   8.250   1.6121   0.01450   0.00866  -0.1687   0.3850   1.0000
   8.500   1.6260   0.01501   0.00910  -0.1660   0.3699   1.0000
   8.750   1.6396   0.01557   0.00960  -0.1634   0.3535   1.0000
   9.000   1.6522   0.01620   0.01016  -0.1606   0.3362   1.0000
   9.250   1.6640   0.01690   0.01078  -0.1578   0.3177   1.0000
   9.500   1.6742   0.01769   0.01150  -0.1548   0.2989   1.0000
   9.750   1.6840   0.01854   0.01228  -0.1519   0.2820   1.0000
  10.000   1.6930   0.01947   0.01313  -0.1489   0.2669   1.0000
  10.250   1.7022   0.02042   0.01403  -0.1460   0.2529   1.0000
  10.500   1.7121   0.02136   0.01495  -0.1434   0.2402   1.0000
  10.750   1.7208   0.02242   0.01597  -0.1406   0.2286   1.0000
  11.000   1.7276   0.02362   0.01714  -0.1378   0.2169   1.0000
  11.250   1.7341   0.02491   0.01840  -0.1351   0.2047   1.0000
  11.500   1.7409   0.02625   0.01972  -0.1326   0.1917   1.0000
  11.750   1.7448   0.02788   0.02129  -0.1300   0.1766   1.0000
  12.000   1.7445   0.02992   0.02325  -0.1271   0.1582   1.0000
  12.250   1.7387   0.03254   0.02574  -0.1241   0.1330   1.0000
  12.500   1.7278   0.03576   0.02879  -0.1210   0.1066   1.0000
  12.750   1.7192   0.03891   0.03185  -0.1184   0.0906   1.0000
  13.000   1.7155   0.04174   0.03466  -0.1163   0.0822   1.0000
  13.250   1.7145   0.04437   0.03731  -0.1145   0.0771   1.0000
  13.500   1.7122   0.04718   0.04014  -0.1128   0.0733   1.0000
  13.750   1.7126   0.04979   0.04281  -0.1114   0.0704   1.0000
  14.000   1.7125   0.05250   0.04557  -0.1101   0.0679   1.0000
  14.250   1.7092   0.05561   0.04872  -0.1087   0.0657   1.0000
  14.500   1.7077   0.05858   0.05176  -0.1076   0.0638   1.0000
  14.750   1.7089   0.06130   0.05456  -0.1066   0.0620   1.0000
  15.000   1.7073   0.06442   0.05774  -0.1057   0.0603   1.0000
  15.250   1.7028   0.06793   0.06130  -0.1049   0.0588   1.0000
  15.500   1.6966   0.07169   0.06513  -0.1041   0.0574   1.0000
  15.750   1.6981   0.07457   0.06810  -0.1035   0.0562   1.0000
  16.000   1.6973   0.07777   0.07139  -0.1031   0.0549   1.0000
  16.250   1.6953   0.08115   0.07483  -0.1027   0.0536   1.0000
  16.500   1.6897   0.08503   0.07876  -0.1024   0.0524   1.0000
  16.750   1.6806   0.08938   0.08317  -0.1021   0.0513   1.0000
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