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FX 62-K-153/20 AIRFOIL (fx62k153-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: FX 62-K-153/20 AIRFOIL (fx62k153-il)
Reynolds number: 50,000
Max Cl/Cd: 26.92 at α=10.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx62k153-il-50000.txt
Download as CSV file: xf-fx62k153-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 62-K-153/20 AIRFOIL                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.4400   0.12200   0.11652  -0.0115   1.0001   0.3283
  -7.500  -0.4488   0.12033   0.11492  -0.0091   1.0001   0.3446
  -7.250  -0.4607   0.11889   0.11356  -0.0065   1.0001   0.3606
  -7.000  -0.4423   0.11511   0.10975  -0.0044   1.0001   0.3795
  -6.750  -0.4361   0.11262   0.10729  -0.0021   1.0001   0.3988
  -6.500  -0.4489   0.11152   0.10626   0.0012   1.0001   0.4199
  -6.250  -0.4350   0.10837   0.10312   0.0033   1.0001   0.4414
  -6.000  -0.4485   0.10758   0.10241   0.0071   1.0001   0.4656
  -5.000  -0.5491   0.06307   0.05664  -0.0522   1.0001   0.1614
  -4.750  -0.5061   0.05612   0.04863  -0.0591   1.0001   0.1313
  -4.500  -0.4646   0.05163   0.04307  -0.0636   1.0001   0.1189
  -4.250  -0.4322   0.04866   0.03956  -0.0658   1.0001   0.1188
  -4.000  -0.3997   0.04641   0.03669  -0.0675   1.0001   0.1199
  -3.750  -0.3707   0.04417   0.03414  -0.0681   1.0001   0.1206
  -3.500  -0.3457   0.04240   0.03232  -0.0680   1.0001   0.1246
  -3.250  -0.3202   0.04139   0.03106  -0.0677   1.0001   0.1327
  -3.000  -0.2988   0.04038   0.03006  -0.0660   1.0001   0.1393
  -2.750  -0.2780   0.03985   0.02943  -0.0641   1.0001   0.1501
  -2.500  -0.2576   0.03918   0.02894  -0.0625   1.0001   0.1687
  -2.250  -0.2230   0.03819   0.02836  -0.0645   1.0001   0.2157
  -1.750  -0.2410   0.04028   0.03320  -0.0406   1.0001   0.7638
  -1.500  -0.2590   0.04068   0.03354  -0.0283   1.0001   0.8091
  -1.250  -0.2736   0.04055   0.03331  -0.0174   1.0001   0.8521
  -1.000  -0.1803   0.04176   0.03379  -0.0201   1.0001   0.9999
  -0.750  -0.1777   0.04140   0.03326  -0.0180   1.0001   0.9999
  -0.500  -0.1749   0.04104   0.03275  -0.0160   1.0001   0.9999
  -0.250  -0.1719   0.04070   0.03227  -0.0140   1.0001   0.9999
   0.000  -0.1683   0.04037   0.03182  -0.0121   1.0001   0.9999
   0.250  -0.1641   0.04007   0.03140  -0.0103   1.0001   0.9999
   0.500  -0.1580   0.03988   0.03107  -0.0089   1.0001   0.9999
   0.750  -0.1477   0.03989   0.03095  -0.0083   1.0001   0.9999
   1.000  -0.1331   0.04015   0.03107  -0.0086   1.0001   0.9999
   1.250  -0.1150   0.04063   0.03141  -0.0095   1.0001   0.9999
   1.500  -0.0942   0.04131   0.03195  -0.0109   1.0001   0.9999
   1.750  -0.0716   0.04216   0.03267  -0.0127   1.0001   0.9999
   2.000  -0.0479   0.04314   0.03353  -0.0148   1.0001   0.9999
   2.250  -0.0234   0.04424   0.03453  -0.0170   1.0001   0.9999
   2.500   0.0015   0.04544   0.03563  -0.0193   1.0001   0.9999
   2.750   0.0266   0.04673   0.03684  -0.0217   1.0001   0.9999
   3.000   0.0517   0.04810   0.03816  -0.0242   1.0001   0.9999
   3.250   0.0766   0.04956   0.03955  -0.0267   1.0001   0.9999
   3.500   0.1027   0.05116   0.04111  -0.0294   0.9993   0.9999
   3.750   0.1428   0.05378   0.04368  -0.0349   0.9932   0.9999
   4.000   0.1884   0.05697   0.04682  -0.0414   0.9855   0.9999
   4.250   0.2229   0.05922   0.04907  -0.0457   0.9747   0.9999
   4.500   0.2552   0.06136   0.05122  -0.0496   0.9628   0.9999
   4.750   0.2854   0.06343   0.05331  -0.0531   0.9502   0.9999
   5.000   0.3143   0.06549   0.05541  -0.0562   0.9374   0.9999
   5.250   0.3428   0.06762   0.05758  -0.0593   0.9241   0.9999
   5.500   0.3709   0.06981   0.05983  -0.0623   0.9108   0.9999
   5.750   0.3987   0.07203   0.06212  -0.0652   0.8970   0.9999
   6.000   0.4260   0.07428   0.06445  -0.0680   0.8826   0.9999
   6.250   0.4528   0.07654   0.06679  -0.0707   0.8675   0.9999
   6.500   0.4801   0.07885   0.06922  -0.0734   0.8515   0.9999
   6.750   0.5101   0.08133   0.07180  -0.0764   0.8346   0.9999
   7.000   0.5523   0.08461   0.07520  -0.0810   0.8164   0.9999
   7.250   0.6053   0.08407   0.07478  -0.0828   0.7562   0.9999
   7.500   0.6598   0.08347   0.07431  -0.0849   0.7128   0.9999
   7.750   0.6773   0.08472   0.07572  -0.0852   0.6924   0.9999
   8.000   0.7175   0.08577   0.07694  -0.0876   0.6730   0.9999
   8.250   0.7453   0.08700   0.07835  -0.0887   0.6543   0.9999
   8.500   0.7662   0.08827   0.07981  -0.0893   0.6347   0.9999
   8.750   0.8184   0.08802   0.07980  -0.0915   0.6144   0.9999
   9.000   0.8349   0.08925   0.08119  -0.0913   0.5938   0.9999
   9.250   0.8685   0.08939   0.08159  -0.0918   0.5738   0.9999
   9.500   0.9211   0.08744   0.07994  -0.0923   0.5536   0.9999
   9.750   0.9381   0.08804   0.08075  -0.0915   0.5308   0.9999
  10.000   1.0248   0.08062   0.07384  -0.0908   0.5106   0.9999
  10.250   1.0455   0.07981   0.07329  -0.0888   0.4853   0.9999
  10.500   1.2404   0.05250   0.04690  -0.0837   0.4471   0.9999
  10.750   1.2840   0.04770   0.04168  -0.0795   0.3701   0.9999
  11.000   1.2879   0.04899   0.04240  -0.0758   0.3113   0.9999
  11.250   1.2952   0.05102   0.04388  -0.0731   0.2633   0.9999
  11.500   1.3068   0.05327   0.04578  -0.0713   0.2263   0.9999
  11.750   1.3246   0.05553   0.04784  -0.0701   0.1966   0.9999
  12.000   1.3553   0.05773   0.04983  -0.0698   0.1709   0.9999
  12.250   1.3777   0.06053   0.05273  -0.0693   0.1535   0.9999
  12.500   1.4049   0.06384   0.05619  -0.0691   0.1394   0.9999
  12.750   1.4232   0.06740   0.05994  -0.0686   0.1284   0.9999
  13.000   1.4315   0.07130   0.06418  -0.0672   0.1216   0.9999
  13.250   1.4329   0.07555   0.06865  -0.0657   0.1156   0.9999
  13.500   1.4125   0.07972   0.07324  -0.0630   0.1136   0.9999
  13.750   1.3927   0.08422   0.07811  -0.0610   0.1117   0.9999
  14.000   1.3725   0.08908   0.08329  -0.0594   0.1102   0.9999
  14.250   1.3460   0.09455   0.08908  -0.0584   0.1102   0.9999
  14.500   1.3130   0.10082   0.09568  -0.0584   0.1115   0.9999
  14.750   1.2798   0.10780   0.10292  -0.0595   0.1132   0.9999
  15.000   1.2482   0.11548   0.11080  -0.0618   0.1148   0.9999
  15.250   1.2198   0.12373   0.11915  -0.0650   0.1163   0.9999
  15.500   1.1954   0.13249   0.12801  -0.0690   0.1174   0.9999
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