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WORTMANN FX 60-126/1 AIRFOIL (fx601261-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 60-126/1 AIRFOIL (fx601261-il)
Reynolds number: 100,000
Max Cl/Cd: 59.42 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx601261-il-100000.txt
Download as CSV file: xf-fx601261-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 60-126/1 AIRFOIL                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3070   0.09639   0.09192  -0.0377   1.0000   0.1240
  -8.000  -0.3180   0.09449   0.09015  -0.0369   1.0000   0.1280
  -7.750  -0.3923   0.09651   0.09248  -0.0347   1.0000   0.1313
  -7.500  -0.3825   0.09279   0.08880  -0.0317   1.0000   0.1327
  -7.250  -0.3790   0.09075   0.08681  -0.0282   1.0000   0.1341
  -7.000  -0.3884   0.08945   0.08558  -0.0247   1.0000   0.1356
  -6.750  -0.4037   0.08843   0.08465  -0.0214   1.0000   0.1373
  -6.500  -0.4221   0.08733   0.08364  -0.0186   1.0000   0.1395
  -6.000  -0.4371   0.05834   0.05431  -0.0590   0.9895   0.0927
  -5.750  -0.3877   0.03884   0.03271  -0.0791   0.9855   0.0479
  -5.500  -0.3457   0.03431   0.02747  -0.0840   0.9807   0.0443
  -5.250  -0.3016   0.03117   0.02355  -0.0876   0.9754   0.0417
  -5.000  -0.2587   0.02914   0.02121  -0.0907   0.9707   0.0415
  -4.750  -0.2231   0.02749   0.01950  -0.0927   0.9639   0.0437
  -4.500  -0.1798   0.02619   0.01809  -0.0957   0.9592   0.0462
  -4.250  -0.1462   0.02508   0.01694  -0.0968   0.9516   0.0480
  -4.000  -0.1027   0.02409   0.01587  -0.0997   0.9463   0.0502
  -3.750  -0.0653   0.02309   0.01482  -0.1021   0.9387   0.0551
  -3.500  -0.0188   0.02203   0.01370  -0.1059   0.9329   0.0717
  -3.250   0.0265   0.02023   0.01329  -0.1107   0.9272   0.3586
  -3.000   0.0643   0.02085   0.01398  -0.1119   0.9185   0.4374
  -2.750   0.0963   0.02153   0.01464  -0.1120   0.9092   0.4786
  -2.500   0.1340   0.02224   0.01544  -0.1124   0.9025   0.5195
  -2.250   0.1616   0.02257   0.01578  -0.1116   0.8929   0.5420
  -2.000   0.2070   0.02234   0.01542  -0.1144   0.8878   0.5591
  -1.750   0.2383   0.02234   0.01535  -0.1148   0.8786   0.5747
  -1.500   0.2824   0.02206   0.01498  -0.1172   0.8731   0.5911
  -1.250   0.3145   0.02194   0.01479  -0.1178   0.8636   0.6042
  -1.000   0.3573   0.02156   0.01433  -0.1200   0.8574   0.6191
  -0.750   0.3867   0.02149   0.01422  -0.1200   0.8470   0.6326
  -0.500   0.4287   0.02108   0.01375  -0.1219   0.8411   0.6469
  -0.250   0.4556   0.02110   0.01372  -0.1217   0.8300   0.6595
   0.000   0.4895   0.02088   0.01349  -0.1223   0.8222   0.6719
   0.250   0.5192   0.02074   0.01335  -0.1222   0.8126   0.6839
   0.500   0.5463   0.02068   0.01330  -0.1217   0.8017   0.6968
   0.750   0.5832   0.02026   0.01285  -0.1224   0.7946   0.7115
   1.000   0.6074   0.02025   0.01287  -0.1214   0.7823   0.7254
   1.250   0.6333   0.02021   0.01285  -0.1207   0.7711   0.7397
   1.500   0.6653   0.01993   0.01257  -0.1207   0.7630   0.7553
   1.750   0.6904   0.01988   0.01257  -0.1199   0.7518   0.7718
   2.000   0.7148   0.01986   0.01261  -0.1189   0.7404   0.7901
   2.250   0.7420   0.01964   0.01241  -0.1181   0.7302   0.8112
   2.500   0.7684   0.01927   0.01209  -0.1169   0.7202   0.8365
   2.750   0.7869   0.01910   0.01204  -0.1145   0.7078   0.8697
   3.250   0.8509   0.01873   0.01174  -0.1159   0.6840   1.0000
   3.500   0.8884   0.01869   0.01157  -0.1177   0.6723   1.0000
   3.750   0.9223   0.01866   0.01145  -0.1185   0.6597   1.0000
   4.000   0.9518   0.01873   0.01144  -0.1186   0.6452   1.0000
   4.250   0.9806   0.01879   0.01143  -0.1185   0.6305   1.0000
   4.500   1.0090   0.01884   0.01143  -0.1181   0.6153   1.0000
   4.750   1.0371   0.01887   0.01139  -0.1177   0.5995   1.0000
   5.000   1.0624   0.01903   0.01152  -0.1170   0.5824   1.0000
   5.250   1.0878   0.01921   0.01170  -0.1162   0.5657   1.0000
   5.500   1.1133   0.01943   0.01191  -0.1155   0.5493   1.0000
   5.750   1.1382   0.01966   0.01212  -0.1147   0.5321   1.0000
   6.000   1.1628   0.01988   0.01233  -0.1138   0.5141   1.0000
   6.250   1.1873   0.02010   0.01247  -0.1129   0.4956   1.0000
   6.500   1.2093   0.02040   0.01278  -0.1117   0.4754   1.0000
   6.750   1.2307   0.02073   0.01312  -0.1104   0.4544   1.0000
   7.000   1.2526   0.02108   0.01340  -0.1091   0.4340   1.0000
   7.250   1.2715   0.02153   0.01389  -0.1075   0.4109   1.0000
   7.500   1.2902   0.02202   0.01430  -0.1059   0.3873   1.0000
   7.750   1.3066   0.02259   0.01482  -0.1040   0.3617   1.0000
   8.000   1.3217   0.02329   0.01549  -0.1019   0.3354   1.0000
   8.250   1.3358   0.02411   0.01623  -0.0998   0.3098   1.0000
   8.500   1.3491   0.02507   0.01702  -0.0976   0.2863   1.0000
   8.750   1.3616   0.02613   0.01805  -0.0955   0.2633   1.0000
   9.000   1.3742   0.02726   0.01907  -0.0934   0.2442   1.0000
   9.250   1.3872   0.02850   0.02017  -0.0914   0.2273   1.0000
   9.500   1.3991   0.02974   0.02138  -0.0894   0.2116   1.0000
   9.750   1.4104   0.03097   0.02256  -0.0872   0.1981   1.0000
  10.000   1.4209   0.03221   0.02383  -0.0850   0.1860   1.0000
  10.250   1.4330   0.03360   0.02527  -0.0831   0.1750   1.0000
  10.500   1.4472   0.03513   0.02681  -0.0816   0.1650   1.0000
  10.750   1.4646   0.03668   0.02826  -0.0806   0.1554   1.0000
  11.000   1.4708   0.03813   0.02994  -0.0781   0.1472   1.0000
  11.250   1.4848   0.03981   0.03161  -0.0768   0.1391   1.0000
  11.500   1.4930   0.04137   0.03325  -0.0749   0.1316   1.0000
  11.750   1.5040   0.04330   0.03526  -0.0734   0.1245   1.0000
  12.000   1.5100   0.04500   0.03707  -0.0715   0.1182   1.0000
  12.250   1.5201   0.04695   0.03905  -0.0702   0.1122   1.0000
  12.500   1.5182   0.04892   0.04128  -0.0680   0.1075   1.0000
  12.750   1.5291   0.05045   0.04270  -0.0670   0.1021   1.0000
  13.000   1.5283   0.05288   0.04541  -0.0653   0.0986   1.0000
  13.250   1.5262   0.05531   0.04810  -0.0638   0.0953   1.0000
  13.500   1.5311   0.05738   0.05025  -0.0628   0.0919   1.0000
  13.750   1.5508   0.05941   0.05218  -0.0625   0.0881   1.0000
  14.000   1.5424   0.06252   0.05565  -0.0612   0.0866   1.0000
  14.250   1.5340   0.06587   0.05932  -0.0603   0.0847   1.0000
  14.500   1.5251   0.06938   0.06312  -0.0597   0.0828   1.0000
  14.750   1.5183   0.07272   0.06665  -0.0596   0.0806   1.0000
  15.000   1.5208   0.07509   0.06904  -0.0595   0.0779   1.0000
  15.250   1.5303   0.07758   0.07152  -0.0593   0.0754   1.0000
  15.500   1.5135   0.08250   0.07679  -0.0600   0.0747   1.0000
  15.750   1.4949   0.08801   0.08262  -0.0613   0.0740   1.0000
  16.000   1.4739   0.09423   0.08916  -0.0633   0.0734   1.0000
  16.250   1.4500   0.10138   0.09660  -0.0661   0.0732   1.0000
  16.500   1.4203   0.11000   0.10552  -0.0703   0.0732   1.0000
  16.750   1.3833   0.12069   0.11648  -0.0764   0.0738   1.0000
  17.000   1.3411   0.13366   0.12966  -0.0843   0.0750   1.0000
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