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FX 63-137 13.7% smoothed (fx63137sm-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX 63-137 13.7% smoothed (fx63137sm-il)
Reynolds number: 200,000
Max Cl/Cd: 91.53 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx63137sm-il-200000.txt
Download as CSV file: xf-fx63137sm-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 63-137 13.7% smoothed                        
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.0995   0.09232   0.08889  -0.0845   0.9554   0.0562
  -8.250  -0.0813   0.08813   0.08469  -0.0901   0.9520   0.0591
  -8.000  -0.0934   0.08050   0.07712  -0.1036   0.9397   0.0620
  -7.750  -0.0602   0.07875   0.07534  -0.1010   0.9391   0.0636
  -7.500  -0.0331   0.07592   0.07250  -0.1041   0.9373   0.0674
  -7.250  -0.0562   0.06513   0.06168  -0.1264   0.9167   0.0719
  -7.000  -0.0146   0.06575   0.06234  -0.1172   0.9226   0.0746
  -6.750  -0.0016   0.06362   0.06021  -0.1176   0.9132   0.0767
  -6.500   0.0116   0.04860   0.04487  -0.1510   0.8999   0.0857
  -6.250   0.0422   0.04696   0.04333  -0.1503   0.8968   0.0880
  -6.000   0.1096   0.02588   0.01987  -0.1803   0.8922   0.0441
  -5.750   0.1451   0.02361   0.01721  -0.1829   0.8862   0.0443
  -5.500   0.1836   0.02169   0.01491  -0.1857   0.8808   0.0456
  -5.250   0.2247   0.01991   0.01297  -0.1887   0.8771   0.0466
  -5.000   0.2643   0.01866   0.01162  -0.1910   0.8730   0.0481
  -4.750   0.2907   0.01793   0.01081  -0.1908   0.8648   0.0500
  -4.500   0.3288   0.01701   0.00979  -0.1927   0.8600   0.0534
  -4.250   0.3625   0.01631   0.00914  -0.1941   0.8541   0.0586
  -4.000   0.3943   0.01561   0.00845  -0.1951   0.8468   0.0642
  -3.750   0.4348   0.01490   0.00775  -0.1979   0.8418   0.0774
  -3.500   0.4726   0.01407   0.00710  -0.2006   0.8350   0.1229
  -3.250   0.5172   0.01294   0.00686  -0.2054   0.8288   0.3733
  -3.000   0.5523   0.01300   0.00688  -0.2065   0.8234   0.4332
  -2.750   0.5777   0.01321   0.00710  -0.2058   0.8153   0.4653
  -2.500   0.6082   0.01338   0.00720  -0.2060   0.8089   0.4942
  -2.250   0.6367   0.01356   0.00735  -0.2057   0.8025   0.5148
  -2.000   0.6637   0.01369   0.00744  -0.2053   0.7949   0.5308
  -1.750   0.6957   0.01377   0.00740  -0.2058   0.7892   0.5464
  -1.500   0.7201   0.01396   0.00761  -0.2048   0.7814   0.5618
  -1.250   0.7480   0.01406   0.00770  -0.2044   0.7747   0.5767
  -1.000   0.7765   0.01413   0.00773  -0.2043   0.7684   0.5873
  -0.750   0.8047   0.01420   0.00773  -0.2043   0.7606   0.5986
  -0.500   0.8346   0.01420   0.00769  -0.2044   0.7549   0.6068
  -0.250   0.8612   0.01429   0.00776  -0.2041   0.7467   0.6171
   0.000   0.8896   0.01430   0.00775  -0.2040   0.7401   0.6254
   0.250   0.9183   0.01437   0.00778  -0.2041   0.7330   0.6355
   0.500   0.9449   0.01442   0.00783  -0.2036   0.7254   0.6442
   0.750   0.9758   0.01445   0.00779  -0.2041   0.7192   0.6542
   1.000   1.0004   0.01454   0.00793  -0.2033   0.7106   0.6635
   1.250   1.0305   0.01456   0.00788  -0.2036   0.7041   0.6733
   1.500   1.0560   0.01468   0.00803  -0.2031   0.6955   0.6839
   1.750   1.0841   0.01470   0.00804  -0.2029   0.6883   0.6931
   2.000   1.1105   0.01481   0.00817  -0.2025   0.6800   0.7044
   2.250   1.1376   0.01486   0.00821  -0.2022   0.6722   0.7146
   2.500   1.1635   0.01496   0.00834  -0.2017   0.6639   0.7252
   2.750   1.1912   0.01503   0.00839  -0.2016   0.6556   0.7375
   3.000   1.2160   0.01514   0.00854  -0.2008   0.6471   0.7485
   3.250   1.2423   0.01521   0.00861  -0.2004   0.6386   0.7601
   3.500   1.2676   0.01533   0.00879  -0.1998   0.6295   0.7730
   3.750   1.2943   0.01543   0.00886  -0.1994   0.6210   0.7869
   4.000   1.3172   0.01555   0.00906  -0.1983   0.6113   0.7998
   4.250   1.3433   0.01564   0.00913  -0.1978   0.6029   0.8140
   4.500   1.3651   0.01577   0.00936  -0.1966   0.5925   0.8295
   4.750   1.3897   0.01588   0.00946  -0.1958   0.5836   0.8463
   5.000   1.4107   0.01596   0.00960  -0.1943   0.5721   0.8654
   5.250   1.4285   0.01600   0.00969  -0.1922   0.5596   0.8873
   5.500   1.4433   0.01596   0.00967  -0.1893   0.5468   0.9200
   5.750   1.4627   0.01598   0.00967  -0.1877   0.5324   1.0000
   6.000   1.4899   0.01628   0.00991  -0.1879   0.5176   1.0000
   6.250   1.5154   0.01662   0.01021  -0.1877   0.5038   1.0000
   6.500   1.5391   0.01697   0.01057  -0.1872   0.4900   1.0000
   6.750   1.5617   0.01736   0.01095  -0.1864   0.4762   1.0000
   7.000   1.5829   0.01777   0.01133  -0.1854   0.4621   1.0000
   7.250   1.6030   0.01822   0.01175  -0.1841   0.4479   1.0000
   7.500   1.6218   0.01871   0.01221  -0.1826   0.4338   1.0000
   7.750   1.6389   0.01924   0.01271  -0.1808   0.4191   1.0000
   8.000   1.6536   0.01981   0.01326  -0.1787   0.4039   1.0000
   8.250   1.6657   0.02041   0.01386  -0.1760   0.3884   1.0000
   8.500   1.6767   0.02110   0.01453  -0.1733   0.3728   1.0000
   8.750   1.6865   0.02186   0.01529  -0.1704   0.3569   1.0000
   9.000   1.6951   0.02273   0.01614  -0.1675   0.3408   1.0000
   9.250   1.7022   0.02372   0.01711  -0.1645   0.3240   1.0000
   9.500   1.7072   0.02488   0.01823  -0.1613   0.3065   1.0000
   9.750   1.7113   0.02617   0.01950  -0.1582   0.2873   1.0000
  10.000   1.7133   0.02769   0.02098  -0.1551   0.2667   1.0000
  10.250   1.7118   0.02956   0.02277  -0.1518   0.2453   1.0000
  10.500   1.7092   0.03168   0.02481  -0.1488   0.2228   1.0000
  10.750   1.7044   0.03414   0.02717  -0.1458   0.2009   1.0000
  11.000   1.6985   0.03689   0.02983  -0.1431   0.1826   1.0000
  11.250   1.6939   0.03972   0.03257  -0.1407   0.1677   1.0000
  11.500   1.6926   0.04238   0.03521  -0.1388   0.1559   1.0000
  11.750   1.6924   0.04504   0.03789  -0.1371   0.1469   1.0000
  12.000   1.6901   0.04799   0.04078  -0.1355   0.1401   1.0000
  12.250   1.6940   0.05042   0.04329  -0.1343   0.1340   1.0000
  12.500   1.6960   0.05308   0.04597  -0.1331   0.1290   1.0000
  12.750   1.6981   0.05582   0.04868  -0.1319   0.1248   1.0000
  13.000   1.7048   0.05810   0.05109  -0.1310   0.1210   1.0000
  13.250   1.7105   0.06050   0.05356  -0.1302   0.1175   1.0000
  13.500   1.7161   0.06296   0.05600  -0.1294   0.1143   1.0000
  13.750   1.7249   0.06509   0.05814  -0.1285   0.1111   1.0000
  14.000   1.7323   0.06741   0.06062  -0.1279   0.1085   1.0000
  14.250   1.7400   0.06969   0.06300  -0.1273   0.1059   1.0000
  14.500   1.7487   0.07187   0.06524  -0.1267   0.1036   1.0000
  14.750   1.7606   0.07368   0.06703  -0.1260   0.1012   1.0000
  15.000   1.7758   0.07522   0.06860  -0.1251   0.0987   1.0000
  15.250   1.7804   0.07794   0.07153  -0.1248   0.0970   1.0000
  15.500   1.7864   0.08051   0.07426  -0.1245   0.0952   1.0000
  15.750   1.7944   0.08285   0.07673  -0.1241   0.0933   1.0000
  16.000   1.8027   0.08513   0.07909  -0.1238   0.0915   1.0000
  16.250   1.8145   0.08697   0.08095  -0.1234   0.0896   1.0000
  16.500   1.8352   0.08806   0.08207  -0.1226   0.0871   1.0000
  16.750   1.8337   0.09152   0.08576  -0.1227   0.0861   1.0000
  17.000   1.8326   0.09501   0.08947  -0.1229   0.0848   1.0000
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