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FX 61-140 AIRFOIL (fx61140-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: FX 61-140 AIRFOIL (fx61140-il)
Reynolds number: 1,000,000
Max Cl/Cd: 118.97 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx61140-il-1000000.txt
Download as CSV file: xf-fx61140-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4488   0.08278   0.08128  -0.0423   1.0000   0.0084
  -9.750  -0.4732   0.07097   0.06945  -0.0506   1.0000   0.0081
  -9.500  -0.5012   0.06374   0.06215  -0.0546   1.0000   0.0078
  -9.250  -0.5271   0.05924   0.05758  -0.0553   1.0000   0.0079
  -9.000  -0.5447   0.05379   0.05200  -0.0591   0.9979   0.0077
  -8.750  -0.5401   0.04747   0.04545  -0.0673   0.9923   0.0079
  -8.500  -0.5544   0.02978   0.02670  -0.0747   0.9854   0.0058
  -8.250  -0.5430   0.02269   0.01888  -0.0758   0.9790   0.0056
  -8.000  -0.5120   0.02065   0.01658  -0.0776   0.9761   0.0061
  -7.750  -0.4777   0.01939   0.01514  -0.0798   0.9740   0.0064
  -7.500  -0.4513   0.01832   0.01392  -0.0801   0.9679   0.0065
  -7.000  -0.3963   0.01449   0.00973  -0.0813   0.9563   0.0068
  -6.500  -0.3309   0.01240   0.00750  -0.0846   0.9399   0.0074
  -6.250  -0.2845   0.01175   0.00682  -0.0890   0.9320   0.0080
  -6.000  -0.2277   0.01090   0.00588  -0.0958   0.9198   0.0087
  -5.750  -0.1688   0.01021   0.00504  -0.1030   0.8960   0.0096
  -5.500  -0.1297   0.00954   0.00412  -0.1060   0.8578   0.0111
  -5.250  -0.1023   0.00939   0.00380  -0.1061   0.8218   0.0127
  -5.000  -0.0767   0.00931   0.00355  -0.1058   0.7900   0.0142
  -4.750  -0.0501   0.00900   0.00311  -0.1059   0.7630   0.0194
  -4.500  -0.0229   0.00880   0.00283  -0.1060   0.7393   0.0282
  -4.000   0.0372   0.00766   0.00216  -0.1085   0.6969   0.1996
  -3.750   0.0745   0.00654   0.00172  -0.1121   0.6784   0.4149
  -3.500   0.1072   0.00620   0.00158  -0.1137   0.6614   0.5103
  -3.250   0.1373   0.00614   0.00153  -0.1143   0.6457   0.5517
  -3.000   0.1667   0.00615   0.00152  -0.1147   0.6311   0.5770
  -2.750   0.1959   0.00620   0.00155  -0.1150   0.6176   0.6015
  -2.500   0.2249   0.00629   0.00159  -0.1152   0.6047   0.6207
  -2.250   0.2536   0.00639   0.00163  -0.1154   0.5928   0.6309
  -2.000   0.2826   0.00649   0.00163  -0.1156   0.5819   0.6380
  -1.750   0.3110   0.00657   0.00167  -0.1157   0.5716   0.6432
  -1.500   0.3398   0.00666   0.00169  -0.1160   0.5616   0.6482
  -1.250   0.3689   0.00674   0.00171  -0.1162   0.5525   0.6529
  -0.750   0.4261   0.00690   0.00179  -0.1166   0.5361   0.6602
  -0.500   0.4547   0.00700   0.00182  -0.1168   0.5283   0.6640
  -0.250   0.4838   0.00707   0.00185  -0.1170   0.5207   0.6673
   0.000   0.5121   0.00715   0.00190  -0.1172   0.5136   0.6701
   0.250   0.5409   0.00722   0.00196  -0.1174   0.5066   0.6730
   0.500   0.5692   0.00732   0.00202  -0.1175   0.4997   0.6760
   0.750   0.5983   0.00739   0.00207  -0.1178   0.4931   0.6791
   1.000   0.6267   0.00750   0.00212  -0.1180   0.4864   0.6818
   1.250   0.6554   0.00755   0.00219  -0.1182   0.4805   0.6843
   1.500   0.6836   0.00764   0.00226  -0.1183   0.4742   0.6867
   1.750   0.7121   0.00773   0.00235  -0.1185   0.4684   0.6891
   2.000   0.7407   0.00781   0.00242  -0.1187   0.4626   0.6916
   2.250   0.7690   0.00793   0.00250  -0.1189   0.4568   0.6939
   2.500   0.7979   0.00799   0.00258  -0.1192   0.4515   0.6960
   2.750   0.8260   0.00807   0.00266  -0.1193   0.4454   0.6981
   3.000   0.8541   0.00816   0.00277  -0.1194   0.4398   0.7001
   3.250   0.8823   0.00825   0.00287  -0.1196   0.4336   0.7021
   3.500   0.9101   0.00838   0.00299  -0.1196   0.4272   0.7044
   3.750   0.9386   0.00847   0.00310  -0.1198   0.4212   0.7066
   4.000   0.9665   0.00861   0.00322  -0.1200   0.4149   0.7086
   4.250   0.9948   0.00869   0.00334  -0.1202   0.4087   0.7106
   4.500   1.0223   0.00881   0.00346  -0.1202   0.4011   0.7125
   4.750   1.0501   0.00892   0.00360  -0.1203   0.3927   0.7143
   5.000   1.0774   0.00907   0.00374  -0.1203   0.3803   0.7163
   5.250   1.1040   0.00928   0.00388  -0.1202   0.3607   0.7183
   5.500   1.1306   0.00951   0.00407  -0.1201   0.3446   0.7202
   5.750   1.1570   0.00977   0.00427  -0.1200   0.3259   0.7222
   6.000   1.1826   0.01010   0.00450  -0.1198   0.3022   0.7238
   6.250   1.2075   0.01046   0.00477  -0.1195   0.2759   0.7257
   6.500   1.2313   0.01094   0.00513  -0.1190   0.2450   0.7274
   6.750   1.2524   0.01168   0.00563  -0.1181   0.1985   0.7292
   7.000   1.2692   0.01284   0.00641  -0.1166   0.1335   0.7311
   7.250   1.2861   0.01396   0.00722  -0.1151   0.0814   0.7330
   7.500   1.3044   0.01492   0.00797  -0.1138   0.0460   0.7348
   7.750   1.3244   0.01569   0.00861  -0.1127   0.0263   0.7367
   8.250   1.3648   0.01706   0.00991  -0.1106   0.0072   0.7402
   8.500   1.3851   0.01769   0.01056  -0.1095   0.0048   0.7420
   8.750   1.4053   0.01828   0.01121  -0.1085   0.0041   0.7438
   9.000   1.4233   0.01903   0.01203  -0.1070   0.0035   0.7457
   9.250   1.4415   0.01971   0.01279  -0.1056   0.0033   0.7476
   9.500   1.4587   0.02041   0.01358  -0.1041   0.0031   0.7496
   9.750   1.4739   0.02119   0.01443  -0.1023   0.0030   0.7514
  10.000   1.4847   0.02198   0.01531  -0.0997   0.0029   0.7531
  10.250   1.4930   0.02287   0.01631  -0.0968   0.0028   0.7550
  10.500   1.5001   0.02387   0.01741  -0.0938   0.0027   0.7568
  10.750   1.5055   0.02500   0.01864  -0.0908   0.0027   0.7587
  11.000   1.5097   0.02628   0.02002  -0.0880   0.0026   0.7609
  11.250   1.5119   0.02777   0.02162  -0.0852   0.0026   0.7630
  11.500   1.5126   0.02950   0.02346  -0.0826   0.0026   0.7650
  11.750   1.5126   0.03146   0.02552  -0.0805   0.0025   0.7667
  12.000   1.5114   0.03371   0.02789  -0.0787   0.0025   0.7688
  12.250   1.5087   0.03633   0.03064  -0.0774   0.0025   0.7707
  12.500   1.5059   0.03921   0.03365  -0.0765   0.0025   0.7727
  12.750   1.5018   0.04247   0.03704  -0.0760   0.0025   0.7747
  13.000   1.4977   0.04596   0.04065  -0.0758   0.0025   0.7768
  13.250   1.4931   0.04969   0.04450  -0.0760   0.0025   0.7787
  13.500   1.4869   0.05378   0.04871  -0.0764   0.0025   0.7803
  13.750   1.4823   0.05781   0.05287  -0.0771   0.0025   0.7820
  14.000   1.4758   0.06221   0.05740  -0.0779   0.0025   0.7837
  14.250   1.4704   0.06659   0.06192  -0.0789   0.0024   0.7853
  14.500   1.4644   0.07120   0.06665  -0.0801   0.0024   0.7869
  14.750   1.4574   0.07608   0.07165  -0.0814   0.0024   0.7885
  15.000   1.4536   0.08063   0.07630  -0.0829   0.0024   0.7902
  15.250   1.4472   0.08571   0.08151  -0.0846   0.0024   0.7919
  15.500   1.4412   0.09082   0.08672  -0.0865   0.0023   0.7935
  15.750   1.4350   0.09610   0.09212  -0.0884   0.0023   0.7949
  16.000   1.4298   0.10135   0.09750  -0.0906   0.0023   0.7968
  16.250   1.4219   0.10711   0.10339  -0.0930   0.0023   0.7982
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