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FX 61-140 AIRFOIL (fx61140-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: FX 61-140 AIRFOIL (fx61140-il)
Reynolds number: 500,000
Max Cl/Cd: 96.49 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx61140-il-500000-n5.txt
Download as CSV file: xf-fx61140-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 61-140 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4693   0.08258   0.08039  -0.0437   1.0000   0.0039
 -10.250  -0.4944   0.06981   0.06761  -0.0521   1.0000   0.0038
 -10.000  -0.5229   0.06170   0.05940  -0.0569   1.0000   0.0037
  -9.750  -0.5482   0.05639   0.05401  -0.0583   1.0000   0.0037
  -9.500  -0.5728   0.05240   0.04992  -0.0578   0.9999   0.0037
  -9.250  -0.5846   0.04560   0.04284  -0.0634   0.9937   0.0036
  -9.000  -0.5913   0.03554   0.03218  -0.0699   0.9850   0.0035
  -8.750  -0.5928   0.02734   0.02315  -0.0712   0.9756   0.0035
  -8.500  -0.5736   0.02400   0.01937  -0.0719   0.9690   0.0036
  -8.250  -0.5503   0.02161   0.01662  -0.0725   0.9619   0.0037
  -8.000  -0.5273   0.01991   0.01469  -0.0726   0.9534   0.0039
  -7.500  -0.4698   0.01732   0.01174  -0.0745   0.9371   0.0042
  -7.250  -0.4354   0.01604   0.01035  -0.0768   0.9285   0.0046
  -7.000  -0.3931   0.01523   0.00947  -0.0805   0.9194   0.0051
  -6.750  -0.3443   0.01434   0.00846  -0.0855   0.9077   0.0057
  -6.500  -0.2859   0.01346   0.00741  -0.0928   0.8910   0.0064
  -6.250  -0.2379   0.01286   0.00668  -0.0977   0.8632   0.0078
  -6.000  -0.2031   0.01252   0.00618  -0.0996   0.8317   0.0090
  -5.750  -0.1751   0.01225   0.00571  -0.1000   0.8010   0.0100
  -5.500  -0.1491   0.01182   0.00511  -0.1002   0.7736   0.0114
  -5.250  -0.1230   0.01161   0.00478  -0.1001   0.7498   0.0135
  -5.000  -0.0965   0.01139   0.00441  -0.1001   0.7284   0.0155
  -4.750  -0.0695   0.01110   0.00400  -0.1003   0.7083   0.0196
  -4.500  -0.0422   0.01091   0.00370  -0.1005   0.6897   0.0250
  -4.250  -0.0142   0.01065   0.00343  -0.1009   0.6731   0.0428
  -4.000   0.0150   0.01022   0.00311  -0.1019   0.6574   0.0914
  -3.750   0.0477   0.00936   0.00269  -0.1042   0.6431   0.2292
  -3.500   0.0842   0.00840   0.00228  -0.1075   0.6294   0.4028
  -3.250   0.1178   0.00800   0.00214  -0.1094   0.6165   0.5071
  -3.000   0.1486   0.00791   0.00217  -0.1102   0.6046   0.5701
  -2.750   0.1778   0.00797   0.00224  -0.1104   0.5940   0.6012
  -2.500   0.2066   0.00806   0.00225  -0.1106   0.5837   0.6142
  -2.000   0.2642   0.00822   0.00224  -0.1110   0.5639   0.6286
  -1.750   0.2929   0.00831   0.00226  -0.1112   0.5551   0.6344
  -1.500   0.3220   0.00839   0.00223  -0.1115   0.5459   0.6398
  -1.250   0.3504   0.00846   0.00226  -0.1116   0.5376   0.6435
  -1.000   0.3789   0.00856   0.00229  -0.1118   0.5296   0.6479
  -0.750   0.4081   0.00863   0.00229  -0.1121   0.5218   0.6523
  -0.500   0.4367   0.00872   0.00232  -0.1123   0.5147   0.6555
  -0.250   0.4653   0.00879   0.00237  -0.1125   0.5079   0.6585
   0.000   0.4938   0.00889   0.00242  -0.1127   0.5018   0.6620
   0.250   0.5228   0.00897   0.00246  -0.1130   0.4955   0.6660
   0.500   0.5515   0.00906   0.00250  -0.1132   0.4889   0.6691
   0.750   0.5798   0.00914   0.00258  -0.1134   0.4830   0.6714
   1.000   0.6083   0.00923   0.00266  -0.1136   0.4769   0.6740
   1.250   0.6367   0.00933   0.00273  -0.1137   0.4711   0.6767
   1.500   0.6654   0.00942   0.00280  -0.1140   0.4644   0.6794
   2.000   0.7223   0.00961   0.00297  -0.1144   0.4525   0.6843
   2.250   0.7503   0.00972   0.00308  -0.1145   0.4465   0.6862
   2.500   0.7785   0.00982   0.00319  -0.1147   0.4409   0.6884
   2.750   0.8068   0.00993   0.00332  -0.1149   0.4352   0.6909
   3.000   0.8349   0.01006   0.00344  -0.1150   0.4301   0.6935
   3.250   0.8635   0.01016   0.00355  -0.1153   0.4245   0.6961
   3.500   0.8914   0.01028   0.00370  -0.1154   0.4184   0.6980
   3.750   0.9190   0.01041   0.00386  -0.1154   0.4130   0.6998
   4.000   0.9468   0.01052   0.00402  -0.1155   0.4067   0.7018
   4.250   0.9742   0.01068   0.00418  -0.1156   0.4000   0.7039
   4.500   1.0022   0.01080   0.00436  -0.1157   0.3930   0.7060
   4.750   1.0295   0.01098   0.00454  -0.1157   0.3865   0.7082
   5.000   1.0574   0.01112   0.00471  -0.1159   0.3784   0.7105
   5.250   1.0843   0.01129   0.00491  -0.1158   0.3687   0.7122
   5.500   1.1106   0.01151   0.00514  -0.1157   0.3536   0.7138
   5.750   1.1344   0.01192   0.00540  -0.1152   0.3182   0.7156
   6.000   1.1571   0.01249   0.00577  -0.1145   0.2766   0.7175
   6.250   1.1796   0.01310   0.00620  -0.1139   0.2377   0.7196
   6.500   1.1981   0.01413   0.00687  -0.1128   0.1766   0.7216
   6.750   1.2153   0.01528   0.00770  -0.1115   0.1179   0.7237
   7.000   1.2337   0.01627   0.00849  -0.1103   0.0773   0.7256
   7.250   1.2517   0.01721   0.00927  -0.1090   0.0466   0.7272
   7.500   1.2699   0.01809   0.01005  -0.1077   0.0248   0.7290
   7.750   1.2884   0.01891   0.01082  -0.1065   0.0126   0.7309
   8.000   1.3069   0.01968   0.01158  -0.1052   0.0048   0.7327
   8.250   1.3260   0.02038   0.01232  -0.1040   0.0034   0.7346
   8.500   1.3453   0.02101   0.01303  -0.1029   0.0030   0.7366
   8.750   1.3632   0.02171   0.01383  -0.1016   0.0028   0.7387
   9.000   1.3793   0.02247   0.01468  -0.1000   0.0025   0.7404
   9.250   1.3920   0.02325   0.01557  -0.0978   0.0024   0.7420
   9.500   1.4021   0.02412   0.01655  -0.0952   0.0022   0.7437
   9.750   1.4089   0.02522   0.01779  -0.0923   0.0021   0.7456
  10.000   1.4154   0.02639   0.01906  -0.0896   0.0020   0.7477
  10.250   1.4223   0.02758   0.02037  -0.0872   0.0020   0.7499
  10.500   1.4279   0.02892   0.02182  -0.0848   0.0020   0.7520
  10.750   1.4319   0.03047   0.02348  -0.0826   0.0019   0.7539
  11.000   1.4342   0.03226   0.02540  -0.0807   0.0019   0.7555
  11.250   1.4354   0.03430   0.02757  -0.0790   0.0019   0.7572
  11.500   1.4357   0.03662   0.03003  -0.0777   0.0019   0.7591
  11.750   1.4350   0.03926   0.03282  -0.0768   0.0018   0.7612
  12.000   1.4340   0.04213   0.03582  -0.0762   0.0018   0.7633
  12.250   1.4323   0.04528   0.03911  -0.0760   0.0018   0.7654
  12.500   1.4293   0.04876   0.04272  -0.0761   0.0018   0.7672
  12.750   1.4258   0.05246   0.04656  -0.0765   0.0018   0.7687
  13.000   1.4223   0.05629   0.05052  -0.0770   0.0018   0.7702
  13.250   1.4174   0.06041   0.05478  -0.0777   0.0018   0.7717
  13.500   1.4123   0.06469   0.05920  -0.0786   0.0017   0.7733
  13.750   1.4073   0.06906   0.06371  -0.0797   0.0017   0.7749
  14.000   1.4016   0.07366   0.06844  -0.0809   0.0017   0.7765
  14.250   1.3967   0.07830   0.07321  -0.0823   0.0017   0.7782
  14.500   1.3910   0.08318   0.07822  -0.0838   0.0017   0.7799
  14.750   1.3855   0.08814   0.08331  -0.0855   0.0017   0.7815
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