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FX 74-CL6-140 (fx74cl6140-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: FX 74-CL6-140 (fx74cl6140-il)
Reynolds number: 200,000
Max Cl/Cd: 71.99 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx74cl6140-il-200000-n5.txt
Download as CSV file: xf-fx74cl6140-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750   0.0410   0.09433   0.08845  -0.0810   0.5332   0.0239
  -8.500   0.0483   0.09181   0.08591  -0.0822   0.5315   0.0244
  -8.250   0.0542   0.08923   0.08332  -0.0836   0.5299   0.0250
  -8.000   0.0569   0.08660   0.08071  -0.0857   0.5285   0.0253
  -7.750   0.0609   0.08397   0.07813  -0.0876   0.5267   0.0254
  -7.500   0.0647   0.08118   0.07537  -0.0894   0.5251   0.0255
  -7.250   0.0748   0.07854   0.07276  -0.0894   0.5230   0.0257
  -7.000   0.0859   0.07622   0.07044  -0.0893   0.5210   0.0261
  -6.750   0.0935   0.07391   0.06815  -0.0897   0.5193   0.0265
  -6.500   0.0987   0.07167   0.06593  -0.0903   0.5177   0.0270
  -6.250   0.1030   0.06947   0.06375  -0.0912   0.5163   0.0273
  -6.000   0.1109   0.06678   0.06106  -0.0935   0.5149   0.0279
  -5.750   0.1211   0.06383   0.05810  -0.0969   0.5136   0.0283
  -5.500   0.1359   0.05922   0.05345  -0.1054   0.5124   0.0295
  -5.000   0.1738   0.04867   0.04270  -0.1173   0.5099   0.0215
  -4.750   0.1932   0.04644   0.04044  -0.1190   0.5081   0.0207
  -4.500   0.2192   0.04226   0.03609  -0.1236   0.5064   0.0204
  -4.250   0.2509   0.03703   0.03052  -0.1287   0.5047   0.0213
  -4.000   0.2800   0.03371   0.02693  -0.1315   0.5028   0.0208
  -3.750   0.3122   0.02987   0.02268  -0.1344   0.5011   0.0199
  -3.500   0.3469   0.02576   0.01794  -0.1371   0.4996   0.0193
  -3.250   0.3793   0.02337   0.01505  -0.1385   0.4981   0.0194
  -3.000   0.4104   0.02180   0.01307  -0.1394   0.4967   0.0197
  -2.750   0.4408   0.02068   0.01158  -0.1399   0.4953   0.0206
  -2.500   0.4705   0.01987   0.01049  -0.1403   0.4938   0.0222
  -2.250   0.4993   0.01926   0.00982  -0.1406   0.4921   0.0230
  -2.000   0.5282   0.01863   0.00909  -0.1408   0.4902   0.0237
  -1.750   0.5571   0.01811   0.00849  -0.1409   0.4883   0.0245
  -1.500   0.5861   0.01771   0.00800  -0.1411   0.4865   0.0255
  -1.250   0.6152   0.01738   0.00769  -0.1415   0.4849   0.0269
  -1.000   0.6444   0.01719   0.00742  -0.1418   0.4834   0.0297
  -0.750   0.6737   0.01701   0.00723  -0.1422   0.4819   0.0337
  -0.500   0.7032   0.01684   0.00701  -0.1426   0.4804   0.0392
  -0.250   0.7329   0.01668   0.00686  -0.1430   0.4790   0.0557
   0.000   0.7629   0.01649   0.00686  -0.1437   0.4775   0.1318
   0.250   0.7908   0.01547   0.00739  -0.1446   0.4758   0.6429
   0.500   0.8165   0.01566   0.00764  -0.1439   0.4742   0.7257
   0.750   0.8413   0.01580   0.00782  -0.1430   0.4726   0.7640
   1.000   0.8671   0.01594   0.00794  -0.1424   0.4709   0.7888
   1.250   0.8915   0.01602   0.00802  -0.1415   0.4691   0.8110
   1.500   0.9160   0.01608   0.00808  -0.1407   0.4674   0.8343
   1.750   0.9417   0.01616   0.00813  -0.1402   0.4658   0.8477
   2.000   0.9700   0.01631   0.00820  -0.1404   0.4644   0.8533
   2.250   0.9978   0.01646   0.00828  -0.1405   0.4631   0.8582
   2.500   1.0259   0.01663   0.00838  -0.1406   0.4618   0.8638
   2.750   1.0530   0.01682   0.00856  -0.1406   0.4602   0.8709
   3.000   1.0789   0.01699   0.00879  -0.1404   0.4582   0.8806
   3.250   1.1047   0.01715   0.00901  -0.1402   0.4563   0.8939
   3.500   1.1309   0.01729   0.00920  -0.1400   0.4546   0.9229
   3.750   1.1594   0.01748   0.00940  -0.1404   0.4527   1.0000
   4.000   1.1878   0.01772   0.00961  -0.1408   0.4509   1.0000
   4.250   1.2162   0.01794   0.00979  -0.1412   0.4492   1.0000
   4.500   1.2446   0.01816   0.00998  -0.1416   0.4477   1.0000
   4.750   1.2728   0.01841   0.01019  -0.1419   0.4464   1.0000
   5.000   1.3012   0.01868   0.01042  -0.1423   0.4451   1.0000
   5.250   1.3262   0.01904   0.01088  -0.1422   0.4428   1.0000
   5.500   1.3517   0.01938   0.01130  -0.1421   0.4405   1.0000
   5.750   1.3776   0.01971   0.01170  -0.1421   0.4385   1.0000
   6.000   1.4036   0.02001   0.01203  -0.1422   0.4365   1.0000
   6.250   1.4299   0.02026   0.01231  -0.1422   0.4346   1.0000
   6.500   1.4565   0.02049   0.01255  -0.1423   0.4329   1.0000
   6.750   1.4833   0.02072   0.01279  -0.1424   0.4313   1.0000
   7.000   1.5103   0.02098   0.01305  -0.1425   0.4300   1.0000
   7.250   1.5333   0.02143   0.01362  -0.1421   0.4277   1.0000
   7.500   1.5554   0.02189   0.01423  -0.1416   0.4250   1.0000
   7.750   1.5786   0.02228   0.01472  -0.1413   0.4226   1.0000
   8.000   1.6025   0.02263   0.01515  -0.1410   0.4205   1.0000
   8.250   1.6270   0.02292   0.01551  -0.1408   0.4185   1.0000
   8.500   1.6522   0.02315   0.01578  -0.1407   0.4167   1.0000
   8.750   1.6781   0.02336   0.01601  -0.1407   0.4150   1.0000
   9.000   1.6983   0.02390   0.01671  -0.1399   0.4126   1.0000
   9.250   1.7159   0.02454   0.01753  -0.1389   0.4096   1.0000
   9.500   1.7355   0.02502   0.01813  -0.1380   0.4068   1.0000
   9.750   1.7567   0.02537   0.01859  -0.1374   0.4043   1.0000
  10.000   1.7794   0.02564   0.01893  -0.1369   0.4022   1.0000
  10.250   1.8036   0.02583   0.01917  -0.1367   0.4003   1.0000
  10.500   1.8166   0.02657   0.02010  -0.1350   0.3971   1.0000
  10.750   1.8269   0.02736   0.02108  -0.1330   0.3935   1.0000
  11.000   1.8413   0.02785   0.02170  -0.1314   0.3902   1.0000
  11.250   1.8584   0.02810   0.02203  -0.1301   0.3874   1.0000
  11.500   1.8696   0.02849   0.02250  -0.1280   0.3836   1.0000
  11.750   1.8600   0.02982   0.02403  -0.1235   0.3780   1.0000
  12.000   1.8721   0.02993   0.02415  -0.1217   0.3719   1.0000
  12.250   1.8564   0.03211   0.02651  -0.1179   0.3654   1.0000
  12.500   1.8593   0.03318   0.02761  -0.1160   0.3578   1.0000
  12.750   1.8360   0.03691   0.03152  -0.1135   0.3507   1.0000
  13.000   1.8337   0.03904   0.03366  -0.1123   0.3421   1.0000
  13.250   1.7957   0.04548   0.04029  -0.1112   0.3345   1.0000
  13.500   1.7803   0.04974   0.04460  -0.1108   0.3258   1.0000
  13.750   1.7577   0.05508   0.05000  -0.1105   0.3167   1.0000
  14.000   1.7250   0.06195   0.05698  -0.1106   0.3079   1.0000
  14.250   1.7229   0.06492   0.05996  -0.1103   0.2988   1.0000
  14.500   1.7018   0.07063   0.06575  -0.1106   0.2897   1.0000
  14.750   1.6909   0.07512   0.07031  -0.1109   0.2812   1.0000
  15.000   1.6938   0.07767   0.07286  -0.1109   0.2719   1.0000
  15.250   1.6786   0.08301   0.07828  -0.1115   0.2619   1.0000
  15.500   1.6719   0.08717   0.08248  -0.1120   0.2516   1.0000
  15.750   1.6681   0.09093   0.08627  -0.1125   0.2404   1.0000
  16.000   1.6634   0.09486   0.09019  -0.1130   0.2280   1.0000
  16.250   1.6566   0.09918   0.09450  -0.1138   0.2148   1.0000
  16.500   1.6491   0.10367   0.09896  -0.1146   0.2007   1.0000
  16.750   1.6403   0.10840   0.10366  -0.1156   0.1862   1.0000
  17.000   1.6307   0.11332   0.10854  -0.1168   0.1717   1.0000
  17.250   1.6206   0.11842   0.11359  -0.1182   0.1573   1.0000
  17.500   1.6099   0.12366   0.11879  -0.1197   0.1432   1.0000
  17.750   1.5996   0.12893   0.12400  -0.1214   0.1290   1.0000
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