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FX 74-CL6-140 (fx74cl6140-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: FX 74-CL6-140 (fx74cl6140-il)
Reynolds number: 1,000,000
Max Cl/Cd: 158.58 at α=9°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx74cl6140-il-1000000-n5.txt
Download as CSV file: xf-fx74cl6140-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 74-CL6-140                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750   0.0583   0.08587   0.08180  -0.0899   0.4710   0.0062
  -8.500   0.0655   0.08325   0.07919  -0.0909   0.4698   0.0064
  -8.250   0.0720   0.08040   0.07635  -0.0921   0.4688   0.0070
  -8.000   0.0784   0.07782   0.07379  -0.0930   0.4676   0.0067
  -7.750   0.0846   0.07522   0.07120  -0.0940   0.4665   0.0066
  -7.500   0.0881   0.07198   0.06798  -0.0953   0.4655   0.0071
  -7.250   0.0948   0.06987   0.06588  -0.0959   0.4643   0.0067
  -7.000   0.0977   0.06707   0.06310  -0.0968   0.4631   0.0069
  -6.750   0.0976   0.06442   0.06048  -0.0971   0.4619   0.0069
  -6.500   0.0993   0.06155   0.05764  -0.0986   0.4609   0.0069
  -6.000   0.0968   0.01793   0.01255  -0.1408   0.4613   0.0076
  -5.750   0.1253   0.01667   0.01107  -0.1417   0.4603   0.0077
  -5.500   0.1540   0.01591   0.01018  -0.1423   0.4592   0.0079
  -5.250   0.1829   0.01520   0.00933  -0.1428   0.4580   0.0080
  -5.000   0.2119   0.01445   0.00843  -0.1433   0.4568   0.0082
  -4.750   0.2410   0.01376   0.00759  -0.1437   0.4556   0.0084
  -4.500   0.2701   0.01323   0.00693  -0.1441   0.4543   0.0087
  -4.250   0.2992   0.01278   0.00635  -0.1443   0.4530   0.0090
  -4.000   0.3283   0.01234   0.00579  -0.1446   0.4516   0.0094
  -3.750   0.3575   0.01194   0.00529  -0.1449   0.4502   0.0096
  -3.500   0.3865   0.01166   0.00491  -0.1451   0.4487   0.0098
  -3.250   0.4158   0.01115   0.00432  -0.1454   0.4470   0.0102
  -3.000   0.4447   0.01092   0.00404  -0.1457   0.4453   0.0104
  -2.750   0.4740   0.01071   0.00380  -0.1459   0.4445   0.0107
  -2.500   0.5033   0.01052   0.00358  -0.1462   0.4437   0.0111
  -2.250   0.5326   0.01034   0.00337  -0.1464   0.4428   0.0114
  -2.000   0.5620   0.01018   0.00318  -0.1467   0.4417   0.0117
  -1.750   0.5913   0.01004   0.00302  -0.1469   0.4404   0.0121
  -1.500   0.6205   0.00993   0.00289  -0.1472   0.4390   0.0125
  -1.250   0.6499   0.00979   0.00273  -0.1475   0.4377   0.0132
  -1.000   0.6791   0.00970   0.00263  -0.1477   0.4364   0.0137
  -0.750   0.7082   0.00964   0.00255  -0.1479   0.4352   0.0145
  -0.500   0.7372   0.00960   0.00248  -0.1481   0.4339   0.0155
  -0.250   0.7662   0.00957   0.00244  -0.1483   0.4324   0.0172
   0.000   0.7950   0.00955   0.00241  -0.1485   0.4307   0.0220
   0.250   0.8239   0.00951   0.00241  -0.1487   0.4293   0.0382
   0.500   0.8533   0.00941   0.00243  -0.1491   0.4285   0.0780
   0.750   0.8826   0.00933   0.00245  -0.1495   0.4276   0.1227
   1.000   0.9121   0.00920   0.00249  -0.1499   0.4264   0.2021
   1.250   0.9436   0.00843   0.00266  -0.1515   0.4251   0.6117
   1.500   0.9720   0.00845   0.00279  -0.1515   0.4237   0.6832
   1.750   1.0004   0.00852   0.00286  -0.1516   0.4224   0.6977
   2.000   1.0288   0.00859   0.00292  -0.1517   0.4210   0.7082
   2.250   1.0570   0.00868   0.00299  -0.1518   0.4194   0.7219
   2.500   1.0850   0.00875   0.00307  -0.1518   0.4179   0.7311
   2.750   1.1131   0.00884   0.00314  -0.1519   0.4164   0.7357
   3.000   1.1410   0.00895   0.00322  -0.1520   0.4147   0.7373
   3.250   1.1694   0.00902   0.00329  -0.1521   0.4136   0.7389
   3.500   1.1977   0.00909   0.00336  -0.1523   0.4124   0.7407
   3.750   1.2259   0.00915   0.00345  -0.1524   0.4111   0.7427
   4.000   1.2539   0.00922   0.00353  -0.1526   0.4096   0.7447
   4.250   1.2819   0.00930   0.00362  -0.1527   0.4080   0.7467
   4.500   1.3098   0.00939   0.00371  -0.1528   0.4062   0.7487
   4.750   1.3375   0.00948   0.00381  -0.1530   0.4045   0.7508
   5.000   1.3651   0.00959   0.00392  -0.1530   0.4029   0.7530
   5.250   1.3924   0.00971   0.00403  -0.1531   0.4010   0.7551
   5.500   1.4197   0.00983   0.00417  -0.1532   0.3992   0.7575
   5.750   1.4474   0.00991   0.00429  -0.1533   0.3978   0.7604
   6.000   1.4749   0.00999   0.00441  -0.1534   0.3963   0.7634
   6.250   1.5022   0.01009   0.00455  -0.1535   0.3946   0.7664
   6.500   1.5294   0.01020   0.00469  -0.1536   0.3925   0.7695
   7.000   1.5831   0.01044   0.00498  -0.1537   0.3882   0.7764
   7.250   1.6094   0.01059   0.00515  -0.1537   0.3861   0.7808
   7.500   1.6361   0.01071   0.00532  -0.1537   0.3842   0.7857
   7.750   1.6629   0.01082   0.00549  -0.1538   0.3822   0.7910
   8.000   1.6894   0.01093   0.00567  -0.1538   0.3797   0.7978
   8.500   1.7412   0.01120   0.00606  -0.1537   0.3743   0.8191
   8.750   1.7659   0.01136   0.00628  -0.1534   0.3712   0.8398
   9.000   1.7888   0.01128   0.00644  -0.1527   0.3679   1.0000
   9.250   1.8137   0.01150   0.00666  -0.1525   0.3605   1.0000
   9.500   1.8376   0.01177   0.00692  -0.1522   0.3515   1.0000
   9.750   1.8601   0.01212   0.00725  -0.1517   0.3413   1.0000
  10.000   1.8813   0.01256   0.00764  -0.1510   0.3286   1.0000
  10.250   1.9009   0.01307   0.00810  -0.1500   0.3140   1.0000
  10.500   1.9184   0.01370   0.00867  -0.1488   0.2971   1.0000
  10.750   1.9324   0.01449   0.00937  -0.1470   0.2773   1.0000
  11.000   1.9442   0.01534   0.01014  -0.1449   0.2600   1.0000
  11.250   1.9529   0.01621   0.01095  -0.1423   0.2444   1.0000
  11.500   1.9529   0.01722   0.01190  -0.1382   0.2271   1.0000
  11.750   1.9466   0.01852   0.01314  -0.1334   0.2092   1.0000
  12.000   1.9358   0.02019   0.01476  -0.1286   0.1932   1.0000
  12.250   1.9217   0.02235   0.01690  -0.1243   0.1792   1.0000
  12.500   1.9062   0.02510   0.01966  -0.1209   0.1674   1.0000
  12.750   1.8891   0.02862   0.02322  -0.1186   0.1573   1.0000
  13.000   1.8689   0.03309   0.02775  -0.1171   0.1483   1.0000
  13.250   1.8480   0.03807   0.03279  -0.1162   0.1400   1.0000
  13.500   1.8260   0.04333   0.03811  -0.1155   0.1327   1.0000
  13.750   1.8015   0.04894   0.04378  -0.1149   0.1259   1.0000
  14.000   1.7799   0.05429   0.04919  -0.1145   0.1189   1.0000
  14.250   1.7574   0.05988   0.05483  -0.1142   0.1122   1.0000
  14.500   1.7386   0.06527   0.06025  -0.1143   0.1041   1.0000
  14.750   1.7224   0.07052   0.06551  -0.1146   0.0955   1.0000
  15.000   1.7077   0.07574   0.07074  -0.1150   0.0867   1.0000
  15.250   1.6934   0.08108   0.07608  -0.1156   0.0779   1.0000
  15.500   1.6813   0.08619   0.08119  -0.1163   0.0691   1.0000
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