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WORTMANN FX 60-126/1 AIRFOIL (fx601261-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 60-126/1 AIRFOIL (fx601261-il)
Reynolds number: 500,000
Max Cl/Cd: 108.18 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx601261-il-500000.txt
Download as CSV file: xf-fx601261-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3491   0.08618   0.08405  -0.0453   1.0000   0.0206
  -9.000  -0.3522   0.08314   0.08106  -0.0454   1.0000   0.0209
  -8.750  -0.3609   0.08001   0.07799  -0.0451   1.0000   0.0212
  -8.500  -0.3520   0.07339   0.07139  -0.0524   0.9970   0.0218
  -8.250  -0.3760   0.04786   0.04556  -0.0889   0.9737   0.0210
  -8.000  -0.3544   0.04167   0.03910  -0.1018   0.9603   0.0218
  -5.750  -0.0763   0.00536   0.00024  -0.1271   0.8625   0.0351
  -5.500  -0.0409   0.01496   0.00902  -0.1312   0.8716   0.0151
  -5.250  -0.0160   0.01357   0.00766  -0.1307   0.8628   0.0141
  -5.000   0.0118   0.01274   0.00673  -0.1308   0.8549   0.0134
  -4.750   0.0386   0.01208   0.00600  -0.1306   0.8459   0.0130
  -4.500   0.0671   0.01153   0.00535  -0.1307   0.8385   0.0128
  -4.250   0.0950   0.01103   0.00478  -0.1308   0.8305   0.0130
  -4.000   0.1239   0.01063   0.00428  -0.1310   0.8235   0.0134
  -3.750   0.1522   0.01028   0.00387  -0.1310   0.8156   0.0141
  -3.500   0.1811   0.01006   0.00353  -0.1311   0.8086   0.0149
  -3.250   0.2093   0.00976   0.00314  -0.1310   0.8000   0.0168
  -3.000   0.2379   0.00959   0.00287  -0.1310   0.7922   0.0201
  -2.750   0.2666   0.00915   0.00259  -0.1312   0.7835   0.0728
  -2.500   0.2959   0.00814   0.00228  -0.1323   0.7756   0.2751
  -2.250   0.3243   0.00789   0.00226  -0.1325   0.7674   0.3597
  -2.000   0.3525   0.00785   0.00225  -0.1324   0.7590   0.3917
  -1.750   0.3807   0.00785   0.00226  -0.1323   0.7504   0.4208
  -1.500   0.4087   0.00787   0.00228  -0.1322   0.7410   0.4436
  -1.250   0.4367   0.00790   0.00228  -0.1320   0.7319   0.4578
  -1.000   0.4646   0.00791   0.00226  -0.1318   0.7216   0.4677
  -0.750   0.4926   0.00794   0.00226  -0.1316   0.7115   0.4783
  -0.500   0.5204   0.00799   0.00226  -0.1314   0.7020   0.4884
  -0.250   0.5482   0.00801   0.00227  -0.1312   0.6914   0.4975
   0.250   0.6033   0.00810   0.00229  -0.1307   0.6669   0.5156
   0.500   0.6303   0.00816   0.00230  -0.1304   0.6512   0.5243
   0.750   0.6572   0.00823   0.00232  -0.1300   0.6347   0.5324
   1.000   0.6842   0.00831   0.00234  -0.1297   0.6192   0.5402
   1.250   0.7114   0.00839   0.00239  -0.1294   0.6059   0.5482
   1.500   0.7386   0.00847   0.00246  -0.1292   0.5929   0.5562
   1.750   0.7657   0.00857   0.00253  -0.1289   0.5802   0.5657
   2.000   0.7927   0.00867   0.00261  -0.1286   0.5672   0.5752
   2.250   0.8195   0.00878   0.00269  -0.1283   0.5544   0.5853
   2.500   0.8463   0.00889   0.00280  -0.1280   0.5403   0.5952
   2.750   0.8726   0.00902   0.00290  -0.1277   0.5231   0.6049
   3.000   0.8989   0.00917   0.00301  -0.1273   0.5044   0.6161
   3.500   0.9514   0.00946   0.00329  -0.1266   0.4720   0.6409
   3.750   0.9775   0.00961   0.00344  -0.1262   0.4563   0.6547
   4.000   1.0035   0.00977   0.00360  -0.1258   0.4405   0.6708
   4.250   1.0290   0.00995   0.00380  -0.1253   0.4228   0.6906
   4.500   1.0541   0.01014   0.00401  -0.1248   0.4054   0.7154
   4.750   1.0790   0.01031   0.00423  -0.1243   0.3875   0.7493
   5.000   1.1027   0.01043   0.00446  -0.1234   0.3696   0.8009
   5.250   1.1186   0.01034   0.00459  -0.1207   0.3535   1.0000
   5.500   1.1437   0.01066   0.00483  -0.1202   0.3354   1.0000
   6.000   1.1926   0.01139   0.00539  -0.1192   0.2959   1.0000
   6.250   1.2162   0.01181   0.00571  -0.1185   0.2753   1.0000
   6.500   1.2395   0.01225   0.00606  -0.1178   0.2537   1.0000
   6.750   1.2620   0.01273   0.00643  -0.1170   0.2319   1.0000
   7.000   1.2841   0.01324   0.00684  -0.1162   0.2112   1.0000
   7.250   1.3055   0.01379   0.00728  -0.1152   0.1884   1.0000
   7.500   1.3262   0.01439   0.00777  -0.1142   0.1703   1.0000
   7.750   1.3467   0.01496   0.00826  -0.1131   0.1495   1.0000
   8.000   1.3658   0.01563   0.00880  -0.1118   0.1320   1.0000
   8.250   1.3859   0.01618   0.00931  -0.1107   0.1190   1.0000
   8.500   1.4058   0.01672   0.00982  -0.1095   0.1083   1.0000
   8.750   1.4245   0.01731   0.01037  -0.1082   0.0986   1.0000
   9.000   1.4417   0.01797   0.01097  -0.1066   0.0897   1.0000
   9.250   1.4601   0.01846   0.01148  -0.1052   0.0823   1.0000
   9.500   1.4746   0.01910   0.01209  -0.1032   0.0734   1.0000
  10.000   1.5008   0.02049   0.01342  -0.0988   0.0591   1.0000
  10.250   1.5122   0.02129   0.01421  -0.0965   0.0540   1.0000
  10.500   1.5270   0.02189   0.01488  -0.0948   0.0506   1.0000
  10.750   1.5371   0.02281   0.01577  -0.0925   0.0414   1.0000
  11.000   1.5447   0.02393   0.01683  -0.0902   0.0348   1.0000
  11.250   1.5530   0.02504   0.01794  -0.0880   0.0314   1.0000
  11.500   1.5602   0.02629   0.01920  -0.0859   0.0285   1.0000
  11.750   1.5689   0.02749   0.02045  -0.0841   0.0262   1.0000
  12.000   1.5806   0.02852   0.02158  -0.0827   0.0246   1.0000
  12.250   1.5864   0.03005   0.02314  -0.0810   0.0197   1.0000
  12.500   1.5768   0.03298   0.02597  -0.0784   0.0056   1.0000
  12.750   1.5765   0.03528   0.02833  -0.0768   0.0041   1.0000
  13.000   1.5782   0.03751   0.03066  -0.0754   0.0037   1.0000
  13.250   1.5807   0.03974   0.03300  -0.0743   0.0035   1.0000
  13.500   1.5823   0.04217   0.03555  -0.0734   0.0033   1.0000
  13.750   1.5836   0.04472   0.03822  -0.0727   0.0032   1.0000
  14.000   1.5840   0.04746   0.04109  -0.0721   0.0031   1.0000
  14.250   1.5832   0.05046   0.04422  -0.0718   0.0030   1.0000
  14.500   1.5820   0.05364   0.04754  -0.0716   0.0029   1.0000
  14.750   1.5803   0.05700   0.05105  -0.0717   0.0029   1.0000
  15.000   1.5770   0.06072   0.05491  -0.0720   0.0028   1.0000
  15.250   1.5735   0.06463   0.05896  -0.0726   0.0028   1.0000
  15.500   1.5681   0.06897   0.06345  -0.0735   0.0027   1.0000
  15.750   1.5620   0.07356   0.06819  -0.0746   0.0027   1.0000
  16.000   1.5541   0.07860   0.07338  -0.0761   0.0027   1.0000
  16.250   1.5451   0.08401   0.07895  -0.0779   0.0026   1.0000
  16.500   1.5356   0.08966   0.08474  -0.0800   0.0026   1.0000
  16.750   1.5244   0.09580   0.09104  -0.0825   0.0026   1.0000
  17.000   1.5124   0.10224   0.09763  -0.0852   0.0026   1.0000
  17.250   1.5002   0.10888   0.10443  -0.0883   0.0026   1.0000
  17.500   1.4868   0.11591   0.11161  -0.0917   0.0026   1.0000
  17.750   1.4723   0.12331   0.11917  -0.0955   0.0025   1.0000
  18.000   1.4602   0.13035   0.12635  -0.0992   0.0026   1.0000
  18.250   1.4456   0.13803   0.13417  -0.1035   0.0026   1.0000
  18.500   1.4315   0.14574   0.14203  -0.1079   0.0025   1.0000
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