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


Details Polar file
Airfoil: WORTMANN FX 60-126/1 AIRFOIL (fx601261-il)
Reynolds number: 1,000,000
Max Cl/Cd: 113.27 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx601261-il-1000000.txt
Download as CSV file: xf-fx601261-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2522   0.08193   0.08046  -0.0494   0.9975   0.0098
  -9.750  -0.2523   0.07490   0.07344  -0.0535   0.9947   0.0099
  -9.500  -0.2571   0.06717   0.06572  -0.0576   0.9906   0.0101
  -9.250  -0.3155   0.04457   0.04301  -0.0694   0.9855   0.0094
  -9.000  -0.3539   0.03034   0.02851  -0.0841   0.9621   0.0091
  -8.750  -0.3427   0.02139   0.01920  -0.1058   0.9423   0.0091
  -8.500  -0.3116   0.01696   0.01440  -0.1188   0.9218   0.0094
  -8.250  -0.2936   0.01451   0.01164  -0.1223   0.8990   0.0097
  -8.000  -0.2788   0.01276   0.00961  -0.1233   0.8834   0.0102
  -7.750  -0.2640   0.02440   0.02082  -0.1309   0.8982   0.0109
  -7.500  -0.2457   0.02176   0.01758  -0.1319   0.8825   0.0117
  -7.250  -0.2225   0.02007   0.01589  -0.1320   0.8722   0.0122
  -7.000  -0.1985   0.01892   0.01464  -0.1321   0.8628   0.0127
  -6.750  -0.1734   0.01802   0.01357  -0.1321   0.8544   0.0136
  -6.500  -0.1449   0.01899   0.01431  -0.1319   0.8458   0.0148
  -6.250  -0.1232   0.01573   0.01095  -0.1321   0.8382   0.0163
  -6.000  -0.0970   0.01498   0.01016  -0.1320   0.8304   0.0175
  -5.000   0.0127   0.01157   0.00617  -0.1304   0.8023   0.0116
  -4.750   0.0400   0.01055   0.00508  -0.1303   0.7956   0.0089
  -4.500   0.0683   0.01033   0.00481  -0.1302   0.7887   0.0085
  -4.250   0.0964   0.00983   0.00425  -0.1303   0.7815   0.0083
  -4.000   0.1250   0.00929   0.00366  -0.1306   0.7740   0.0082
  -3.750   0.1536   0.00895   0.00324  -0.1306   0.7661   0.0083
  -3.500   0.1826   0.00848   0.00268  -0.1309   0.7583   0.0088
  -3.250   0.2112   0.00823   0.00235  -0.1309   0.7504   0.0098
  -3.000   0.2400   0.00807   0.00214  -0.1310   0.7422   0.0105
  -2.750   0.2683   0.00797   0.00197  -0.1309   0.7339   0.0111
  -2.500   0.2971   0.00784   0.00181  -0.1310   0.7250   0.0131
  -2.250   0.3257   0.00766   0.00163  -0.1310   0.7164   0.0401
  -2.000   0.3553   0.00688   0.00135  -0.1319   0.7067   0.2049
  -1.750   0.3842   0.00646   0.00127  -0.1324   0.6971   0.3184
  -1.500   0.4125   0.00637   0.00126  -0.1325   0.6867   0.3636
  -1.250   0.4406   0.00638   0.00125  -0.1324   0.6754   0.3841
  -1.000   0.4683   0.00639   0.00128  -0.1322   0.6600   0.4143
  -0.750   0.4958   0.00645   0.00129  -0.1320   0.6418   0.4284
  -0.500   0.5235   0.00651   0.00130  -0.1318   0.6249   0.4378
   0.000   0.5790   0.00665   0.00135  -0.1315   0.5981   0.4542
   0.250   0.6067   0.00673   0.00139  -0.1314   0.5832   0.4645
   0.500   0.6344   0.00682   0.00143  -0.1312   0.5691   0.4750
   0.750   0.6623   0.00688   0.00148  -0.1311   0.5566   0.4837
   1.000   0.6901   0.00697   0.00154  -0.1310   0.5444   0.4928
   1.250   0.7177   0.00706   0.00160  -0.1308   0.5315   0.5024
   1.500   0.7450   0.00718   0.00167  -0.1306   0.5151   0.5099
   1.750   0.7718   0.00733   0.00176  -0.1304   0.4950   0.5174
   2.000   0.7988   0.00748   0.00184  -0.1301   0.4761   0.5249
   2.250   0.8260   0.00761   0.00194  -0.1299   0.4604   0.5334
   2.500   0.8530   0.00776   0.00204  -0.1297   0.4422   0.5418
   2.750   0.8798   0.00792   0.00215  -0.1295   0.4251   0.5513
   3.000   0.9066   0.00809   0.00228  -0.1292   0.4089   0.5608
   3.250   0.9331   0.00827   0.00242  -0.1289   0.3914   0.5705
   3.500   0.9594   0.00848   0.00257  -0.1286   0.3705   0.5805
   3.750   0.9854   0.00871   0.00273  -0.1283   0.3500   0.5909
   4.000   1.0115   0.00893   0.00290  -0.1279   0.3322   0.6021
   4.250   1.0373   0.00917   0.00309  -0.1276   0.3121   0.6142
   4.500   1.0628   0.00943   0.00330  -0.1272   0.2915   0.6270
   4.750   1.0882   0.00970   0.00352  -0.1268   0.2725   0.6410
   5.000   1.1133   0.00999   0.00376  -0.1263   0.2505   0.6581
   5.250   1.1379   0.01031   0.00403  -0.1258   0.2293   0.6799
   5.500   1.1626   0.01059   0.00432  -0.1253   0.2103   0.7086
   5.750   1.1861   0.01097   0.00466  -0.1246   0.1848   0.7486
   6.000   1.2096   0.01122   0.00499  -0.1239   0.1680   0.8102
   6.250   1.2257   0.01127   0.00524  -0.1214   0.1498   1.0000
   6.500   1.2496   0.01168   0.00556  -0.1208   0.1353   1.0000
   6.750   1.2734   0.01207   0.00588  -0.1202   0.1221   1.0000
   7.000   1.2954   0.01260   0.00628  -0.1193   0.1023   1.0000
   7.250   1.3186   0.01302   0.00663  -0.1186   0.0934   1.0000
   7.500   1.3425   0.01336   0.00696  -0.1180   0.0876   1.0000
   7.750   1.3657   0.01374   0.00731  -0.1172   0.0790   1.0000
   8.250   1.4074   0.01481   0.00821  -0.1151   0.0577   1.0000
   8.500   1.4294   0.01522   0.00862  -0.1142   0.0528   1.0000
   8.750   1.4522   0.01555   0.00897  -0.1135   0.0503   1.0000
   9.000   1.4689   0.01630   0.00961  -0.1118   0.0359   1.0000
   9.250   1.4864   0.01695   0.01020  -0.1103   0.0307   1.0000
   9.500   1.5046   0.01750   0.01074  -0.1088   0.0271   1.0000
   9.750   1.5232   0.01791   0.01118  -0.1073   0.0251   1.0000
  10.000   1.5341   0.01867   0.01192  -0.1047   0.0170   1.0000
  10.250   1.5310   0.02022   0.01338  -0.1000   0.0030   1.0000
  10.500   1.5427   0.02096   0.01419  -0.0976   0.0026   1.0000
  10.750   1.5537   0.02177   0.01507  -0.0953   0.0024   1.0000
  11.000   1.5644   0.02262   0.01599  -0.0931   0.0022   1.0000
  11.250   1.5738   0.02359   0.01705  -0.0908   0.0021   1.0000
  11.500   1.5833   0.02460   0.01813  -0.0887   0.0020   1.0000
  11.750   1.5923   0.02570   0.01931  -0.0868   0.0020   1.0000
  12.000   1.6005   0.02691   0.02060  -0.0849   0.0019   1.0000
  12.250   1.6077   0.02826   0.02203  -0.0831   0.0019   1.0000
  12.500   1.6137   0.02978   0.02363  -0.0813   0.0018   1.0000
  12.750   1.6193   0.03140   0.02533  -0.0797   0.0017   1.0000
  13.000   1.6228   0.03328   0.02732  -0.0781   0.0017   1.0000
  13.250   1.6256   0.03532   0.02944  -0.0767   0.0016   1.0000
  13.500   1.6261   0.03768   0.03191  -0.0754   0.0015   1.0000
  13.750   1.6252   0.04028   0.03462  -0.0743   0.0015   1.0000
  14.000   1.6218   0.04329   0.03775  -0.0734   0.0014   1.0000
  14.250   1.6156   0.04676   0.04136  -0.0727   0.0014   1.0000
  14.500   1.6014   0.05141   0.04617  -0.0724   0.0013   1.0000
  14.750   1.5904   0.05598   0.05089  -0.0727   0.0013   1.0000
  15.000   1.5877   0.05963   0.05465  -0.0731   0.0013   1.0000
  15.250   1.5826   0.06382   0.05895  -0.0738   0.0013   1.0000
  15.500   1.5774   0.06819   0.06344  -0.0748   0.0013   1.0000
  15.750   1.5698   0.07310   0.06847  -0.0761   0.0013   1.0000
  16.000   1.5612   0.07837   0.07387  -0.0778   0.0013   1.0000
  16.250   1.5513   0.08407   0.07970  -0.0798   0.0012   1.0000
  16.500   1.5394   0.09029   0.08605  -0.0822   0.0012   1.0000
  16.750   1.5266   0.09687   0.09276  -0.0850   0.0012   1.0000
  17.000   1.5132   0.10378   0.09981  -0.0881   0.0012   1.0000
  17.250   1.4983   0.11114   0.10730  -0.0916   0.0012   1.0000
  17.500   1.4839   0.11855   0.11485  -0.0953   0.0012   1.0000
  17.750   1.4695   0.12614   0.12257  -0.0992   0.0012   1.0000
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