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FX 63-137 13.7% smoothed (fx63137sm-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX 63-137 13.7% smoothed (fx63137sm-il)
Reynolds number: 50,000
Max Cl/Cd: 31.55 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx63137sm-il-50000-n5.txt
Download as CSV file: xf-fx63137sm-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2265   0.11224   0.10581  -0.0522   0.9710   0.0905
  -8.000  -0.2215   0.10587   0.09941  -0.0579   0.9642   0.0687
  -7.500  -0.2216   0.09657   0.09015  -0.0659   0.9469   0.0610
  -7.250  -0.2120   0.09314   0.08674  -0.0680   0.9397   0.0599
  -7.000  -0.2107   0.08987   0.08349  -0.0696   0.9306   0.0590
  -6.750  -0.2036   0.08548   0.07912  -0.0737   0.9235   0.0579
  -6.500  -0.2050   0.08111   0.07477  -0.0770   0.9130   0.0568
  -6.000  -0.1898   0.05944   0.05237  -0.1096   0.8936   0.0526
  -5.750  -0.1629   0.05455   0.04716  -0.1167   0.8876   0.0533
  -5.500  -0.1383   0.05188   0.04432  -0.1200   0.8807   0.0551
  -5.250  -0.0949   0.04749   0.03940  -0.1281   0.8768   0.0574
  -5.000  -0.0445   0.04325   0.03445  -0.1361   0.8742   0.0591
  -4.750  -0.0149   0.04092   0.03160  -0.1386   0.8666   0.0605
  -4.500   0.0237   0.03893   0.02930  -0.1419   0.8621   0.0638
  -4.250   0.0642   0.03736   0.02750  -0.1448   0.8587   0.0687
  -4.000   0.0925   0.03626   0.02603  -0.1452   0.8520   0.0721
  -3.750   0.1227   0.03532   0.02514  -0.1461   0.8461   0.0777
  -3.500   0.1603   0.03425   0.02390  -0.1478   0.8423   0.0860
  -3.250   0.1903   0.03358   0.02314  -0.1486   0.8363   0.0965
  -3.000   0.2230   0.03286   0.02244  -0.1502   0.8298   0.1129
  -2.750   0.2741   0.03142   0.02126  -0.1557   0.8264   0.1614
  -2.500   0.3310   0.03014   0.02113  -0.1623   0.8241   0.3831
  -2.250   0.3494   0.03089   0.02194  -0.1605   0.8149   0.4585
  -2.000   0.3777   0.03134   0.02234  -0.1595   0.8092   0.5115
  -1.750   0.4074   0.03162   0.02253  -0.1584   0.8051   0.5502
  -1.500   0.4174   0.03236   0.02326  -0.1551   0.7946   0.5747
  -1.250   0.4489   0.03242   0.02319  -0.1548   0.7902   0.6019
  -1.000   0.4670   0.03290   0.02357  -0.1533   0.7812   0.6187
  -0.750   0.4986   0.03293   0.02344  -0.1538   0.7754   0.6351
  -0.500   0.5387   0.03269   0.02302  -0.1555   0.7718   0.6509
  -0.250   0.5495   0.03334   0.02365  -0.1531   0.7610   0.6611
   0.000   0.5862   0.03318   0.02336  -0.1543   0.7565   0.6750
   0.250   0.6087   0.03362   0.02371  -0.1540   0.7480   0.6878
   0.500   0.6385   0.03370   0.02371  -0.1543   0.7415   0.7008
   0.750   0.6770   0.03340   0.02332  -0.1556   0.7377   0.7142
   1.000   0.6882   0.03421   0.02413  -0.1536   0.7265   0.7258
   1.250   0.7256   0.03398   0.02382  -0.1548   0.7221   0.7403
   1.500   0.7415   0.03469   0.02453  -0.1535   0.7120   0.7538
   1.750   0.7729   0.03458   0.02439  -0.1538   0.7063   0.7683
   2.250   0.8174   0.03516   0.02498  -0.1521   0.6906   0.7989
   2.500   0.8560   0.03467   0.02447  -0.1532   0.6867   0.8177
   2.750   0.8609   0.03572   0.02558  -0.1503   0.6747   0.8355
   3.000   0.8945   0.03515   0.02503  -0.1504   0.6704   0.8581
   3.250   0.8972   0.03615   0.02613  -0.1472   0.6586   0.8842
   3.500   0.9276   0.03547   0.02547  -0.1467   0.6539   0.9345
   4.000   0.9931   0.03627   0.02624  -0.1497   0.6373   1.0000
   4.250   1.0096   0.03761   0.02760  -0.1494   0.6256   1.0000
   4.500   1.0558   0.03714   0.02709  -0.1519   0.6207   1.0000
   4.750   1.0692   0.03853   0.02851  -0.1509   0.6088   1.0000
   5.000   1.1144   0.03796   0.02794  -0.1530   0.6038   1.0000
   5.250   1.1244   0.03945   0.02947  -0.1515   0.5916   1.0000
   5.500   1.1705   0.03870   0.02871  -0.1533   0.5866   1.0000
   5.750   1.1769   0.04035   0.03044  -0.1513   0.5741   1.0000
   6.000   1.2255   0.03935   0.02945  -0.1533   0.5692   1.0000
   6.250   1.2282   0.04116   0.03134  -0.1508   0.5563   1.0000
   6.500   1.2463   0.04204   0.03229  -0.1499   0.5462   1.0000
   6.750   1.2796   0.04184   0.03216  -0.1501   0.5382   1.0000
   7.000   1.2873   0.04339   0.03379  -0.1482   0.5263   1.0000
   7.250   1.3331   0.04225   0.03269  -0.1494   0.5199   1.0000
   7.500   1.3337   0.04422   0.03480  -0.1468   0.5069   1.0000
   7.750   1.3500   0.04511   0.03578  -0.1455   0.4961   1.0000
   8.000   1.3882   0.04426   0.03498  -0.1458   0.4871   1.0000
   8.250   1.3911   0.04599   0.03683  -0.1434   0.4736   1.0000
   8.500   1.4029   0.04694   0.03785  -0.1416   0.4601   1.0000
   8.750   1.4192   0.04740   0.03837  -0.1400   0.4459   1.0000
   9.000   1.4347   0.04791   0.03891  -0.1383   0.4312   1.0000
   9.250   1.4481   0.04864   0.03970  -0.1366   0.4162   1.0000
   9.500   1.4606   0.04952   0.04061  -0.1350   0.4013   1.0000
   9.750   1.4728   0.05051   0.04163  -0.1334   0.3867   1.0000
  10.000   1.4762   0.05243   0.04365  -0.1316   0.3718   1.0000
  10.250   1.4788   0.05454   0.04586  -0.1300   0.3569   1.0000
  10.500   1.4820   0.05666   0.04806  -0.1285   0.3418   1.0000
  10.750   1.4851   0.05885   0.05032  -0.1271   0.3265   1.0000
  11.000   1.4880   0.06114   0.05268  -0.1258   0.3113   1.0000
  11.250   1.4903   0.06356   0.05514  -0.1246   0.2959   1.0000
  11.500   1.4918   0.06615   0.05777  -0.1236   0.2805   1.0000
  11.750   1.4925   0.06890   0.06057  -0.1226   0.2652   1.0000
  12.000   1.4933   0.07176   0.06345  -0.1218   0.2506   1.0000
  12.250   1.4938   0.07474   0.06644  -0.1211   0.2365   1.0000
  12.500   1.4948   0.07772   0.06941  -0.1205   0.2234   1.0000
  12.750   1.4975   0.08051   0.07214  -0.1199   0.2116   1.0000
  13.000   1.4960   0.08417   0.07592  -0.1198   0.2003   1.0000
  13.250   1.4974   0.08746   0.07926  -0.1196   0.1907   1.0000
  13.500   1.5039   0.08985   0.08158  -0.1192   0.1824   1.0000
  13.750   1.5019   0.09391   0.08583  -0.1195   0.1743   1.0000
  14.250   1.5084   0.10031   0.09240  -0.1198   0.1612   1.0000
  14.500   1.5155   0.10290   0.09504  -0.1198   0.1558   1.0000
  14.750   1.5217   0.10573   0.09795  -0.1199   0.1510   1.0000
  15.000   1.5177   0.11043   0.10292  -0.1211   0.1466   1.0000
  15.250   1.5231   0.11337   0.10595  -0.1215   0.1423   1.0000
  15.500   1.5364   0.11495   0.10752  -0.1212   0.1384   1.0000
  15.750   1.5199   0.12207   0.11501  -0.1241   0.1353   1.0000
  16.000   1.5062   0.12894   0.12215  -0.1270   0.1325   1.0000
  16.250   1.4974   0.13494   0.12835  -0.1297   0.1298   1.0000
  16.500   1.5117   0.13618   0.12964  -0.1295   0.1269   1.0000
  16.750   1.5031   0.14226   0.13588  -0.1325   0.1246   1.0000
  17.000   1.3442   0.18909   0.18298  -0.1639   0.1198   1.0000
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