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FX 74-CL6-140 (fx74cl6140-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: FX 74-CL6-140 (fx74cl6140-il)
Reynolds number: 500,000
Max Cl/Cd: 120.47 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx74cl6140-il-500000-n5.txt
Download as CSV file: xf-fx74cl6140-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750   0.0515   0.08966   0.08489  -0.0854   0.4916   0.0115
  -8.500   0.0571   0.08664   0.08189  -0.0869   0.4905   0.0121
  -8.250   0.0560   0.08294   0.07823  -0.0898   0.4895   0.0124
  -8.000   0.0628   0.08016   0.07548  -0.0906   0.4882   0.0124
  -7.500   0.0828   0.07604   0.07136  -0.0911   0.4853   0.0127
  -7.250   0.0901   0.07376   0.06910  -0.0918   0.4841   0.0129
  -7.000   0.0956   0.07126   0.06661  -0.0927   0.4829   0.0129
  -6.750   0.1009   0.06896   0.06432  -0.0933   0.4818   0.0132
  -6.500   0.1028   0.06663   0.06203  -0.0937   0.4806   0.0132
  -6.250   0.1077   0.06412   0.05953  -0.0952   0.4795   0.0132
  -6.000   0.1236   0.04272   0.03840  -0.0932   0.4767   0.0123
  -5.500   0.1398   0.04742   0.04275  -0.1158   0.4767   0.0097
  -5.250   0.1615   0.04187   0.03708  -0.1222   0.4757   0.0096
  -5.000   0.1892   0.03328   0.02817  -0.1301   0.4747   0.0098
  -4.750   0.2178   0.02859   0.02318  -0.1339   0.4734   0.0101
  -4.500   0.2476   0.02498   0.01926  -0.1365   0.4721   0.0103
  -4.250   0.2793   0.02114   0.01495  -0.1389   0.4708   0.0108
  -4.000   0.3114   0.01810   0.01133  -0.1406   0.4694   0.0117
  -3.750   0.3422   0.01630   0.00910  -0.1415   0.4681   0.0120
  -3.500   0.3721   0.01528   0.00777  -0.1420   0.4667   0.0123
  -3.250   0.4014   0.01452   0.00685  -0.1423   0.4654   0.0126
  -3.000   0.4303   0.01407   0.00631  -0.1426   0.4640   0.0130
  -2.750   0.4592   0.01371   0.00586  -0.1429   0.4625   0.0134
  -2.500   0.4881   0.01339   0.00545  -0.1431   0.4609   0.0139
  -2.250   0.5174   0.01307   0.00509  -0.1434   0.4598   0.0144
  -2.000   0.5467   0.01286   0.00482  -0.1436   0.4586   0.0152
  -1.750   0.5760   0.01257   0.00453  -0.1440   0.4574   0.0159
  -1.500   0.6054   0.01237   0.00431  -0.1443   0.4561   0.0165
  -1.250   0.6347   0.01220   0.00412  -0.1446   0.4547   0.0172
  -1.000   0.6640   0.01207   0.00395  -0.1448   0.4533   0.0181
  -0.750   0.6932   0.01195   0.00382  -0.1451   0.4518   0.0194
  -0.500   0.7223   0.01188   0.00371  -0.1453   0.4503   0.0215
  -0.250   0.7513   0.01182   0.00364  -0.1456   0.4490   0.0262
   0.000   0.7805   0.01173   0.00359  -0.1459   0.4478   0.0450
   0.250   0.8097   0.01165   0.00360  -0.1463   0.4465   0.0884
   0.500   0.8388   0.01159   0.00365  -0.1467   0.4450   0.1471
   0.750   0.8708   0.01066   0.00385  -0.1485   0.4438   0.5863
   1.000   0.8985   0.01070   0.00407  -0.1483   0.4425   0.6932
   1.250   0.9265   0.01079   0.00417  -0.1482   0.4412   0.7174
   1.500   0.9545   0.01087   0.00425  -0.1482   0.4399   0.7311
   1.750   0.9823   0.01096   0.00433  -0.1482   0.4384   0.7456
   2.000   1.0101   0.01104   0.00441  -0.1481   0.4369   0.7593
   2.250   1.0379   0.01112   0.00448  -0.1481   0.4354   0.7679
   2.500   1.0661   0.01122   0.00455  -0.1482   0.4340   0.7709
   2.750   1.0942   0.01132   0.00461  -0.1483   0.4327   0.7730
   3.000   1.1220   0.01143   0.00470  -0.1484   0.4313   0.7750
   3.250   1.1496   0.01157   0.00480  -0.1485   0.4297   0.7776
   3.500   1.1776   0.01166   0.00491  -0.1486   0.4284   0.7805
   3.750   1.2054   0.01176   0.00504  -0.1487   0.4271   0.7834
   4.000   1.2333   0.01186   0.00516  -0.1488   0.4256   0.7862
   4.500   1.2884   0.01206   0.00540  -0.1490   0.4221   0.7919
   4.750   1.3158   0.01216   0.00554  -0.1491   0.4206   0.7954
   5.000   1.3430   0.01228   0.00567  -0.1491   0.4190   0.7996
   5.250   1.3702   0.01240   0.00580  -0.1491   0.4174   0.8042
   5.500   1.3969   0.01253   0.00595  -0.1491   0.4157   0.8090
   5.750   1.4236   0.01269   0.00613  -0.1491   0.4141   0.8146
   6.250   1.4770   0.01291   0.00651  -0.1491   0.4108   0.8291
   6.500   1.5032   0.01301   0.00670  -0.1490   0.4088   0.8401
   6.750   1.5286   0.01310   0.00688  -0.1487   0.4068   0.8584
   7.000   1.5525   0.01307   0.00700  -0.1481   0.4051   1.0000
   7.250   1.5790   0.01324   0.00720  -0.1481   0.4032   1.0000
   7.500   1.6051   0.01343   0.00740  -0.1481   0.4013   1.0000
   7.750   1.6310   0.01364   0.00762  -0.1481   0.3994   1.0000
   8.000   1.6571   0.01382   0.00789  -0.1481   0.3974   1.0000
   8.250   1.6830   0.01401   0.00815  -0.1480   0.3952   1.0000
   8.500   1.7085   0.01420   0.00841  -0.1479   0.3928   1.0000
   8.750   1.7336   0.01439   0.00865  -0.1478   0.3903   1.0000
   9.000   1.7583   0.01460   0.00890  -0.1476   0.3879   1.0000
   9.250   1.7825   0.01484   0.00917  -0.1473   0.3856   1.0000
   9.500   1.8070   0.01507   0.00949  -0.1470   0.3830   1.0000
   9.750   1.8310   0.01529   0.00980  -0.1468   0.3795   1.0000
  10.000   1.8535   0.01550   0.01006  -0.1462   0.3740   1.0000
  10.250   1.8750   0.01575   0.01035  -0.1455   0.3668   1.0000
  10.500   1.8946   0.01606   0.01068  -0.1445   0.3580   1.0000
  10.750   1.9138   0.01642   0.01108  -0.1435   0.3481   1.0000
  11.000   1.9303   0.01689   0.01156  -0.1421   0.3382   1.0000
  11.250   1.9422   0.01750   0.01215  -0.1399   0.3258   1.0000
  11.500   1.9474   0.01826   0.01290  -0.1367   0.3121   1.0000
  11.750   1.9497   0.01919   0.01382  -0.1332   0.2997   1.0000
  12.000   1.9529   0.02018   0.01483  -0.1301   0.2891   1.0000
  12.250   1.9527   0.02143   0.01610  -0.1269   0.2790   1.0000
  12.500   1.9467   0.02317   0.01787  -0.1236   0.2683   1.0000
  12.750   1.9359   0.02554   0.02026  -0.1205   0.2574   1.0000
  13.000   1.9218   0.02862   0.02338  -0.1181   0.2460   1.0000
  13.250   1.9040   0.03256   0.02737  -0.1163   0.2349   1.0000
  13.500   1.8819   0.03742   0.03229  -0.1152   0.2248   1.0000
  13.750   1.8551   0.04306   0.03799  -0.1144   0.2150   1.0000
  14.000   1.8283   0.04887   0.04385  -0.1137   0.2054   1.0000
  14.250   1.8017   0.05473   0.04976  -0.1133   0.1961   1.0000
  14.500   1.7753   0.06076   0.05581  -0.1130   0.1866   1.0000
  14.750   1.7505   0.06689   0.06196  -0.1132   0.1762   1.0000
  15.000   1.7300   0.07270   0.06778  -0.1135   0.1651   1.0000
  15.250   1.7116   0.07842   0.07350  -0.1140   0.1534   1.0000
  15.500   1.6946   0.08411   0.07919  -0.1147   0.1419   1.0000
  15.750   1.6793   0.08969   0.08476  -0.1155   0.1304   1.0000
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