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FX 60-100 (126) AIRFOIL (fx601001-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: FX 60-100 (126) AIRFOIL (fx601001-il)
Reynolds number: 100,000
Max Cl/Cd: 60.97 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx601001-il-100000.txt
Download as CSV file: xf-fx601001-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 60-100 (126) AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3722   0.10326   0.09828  -0.0325   1.0000   0.1031
  -9.000  -0.3741   0.10050   0.09559  -0.0338   1.0000   0.1076
  -8.750  -0.4056   0.09891   0.09420  -0.0394   1.0000   0.1104
  -8.500  -0.3767   0.09403   0.08926  -0.0350   1.0000   0.1139
  -8.250  -0.3714   0.09141   0.08669  -0.0342   1.0000   0.1185
  -8.000  -0.3949   0.08951   0.08496  -0.0364   1.0000   0.1235
  -7.750  -0.4351   0.08731   0.08299  -0.0421   1.0000   0.1246
  -7.500  -0.3875   0.08358   0.07913  -0.0329   1.0000   0.1301
  -7.250  -0.3995   0.08173   0.07740  -0.0313   1.0000   0.1347
  -7.000  -0.4374   0.07763   0.07351  -0.0403   1.0000   0.1393
  -6.750  -0.4183   0.07640   0.07228  -0.0306   1.0000   0.1428
  -6.500  -0.4220   0.07405   0.06999  -0.0301   1.0000   0.1485
  -6.250  -0.4323   0.07012   0.06615  -0.0336   1.0000   0.1558
  -6.000  -0.4165   0.04261   0.03716  -0.0686   1.0000   0.0712
  -5.750  -0.3930   0.03763   0.03177  -0.0707   1.0000   0.0634
  -5.500  -0.3614   0.03217   0.02543  -0.0743   1.0000   0.0591
  -5.250  -0.3362   0.02988   0.02284  -0.0752   1.0000   0.0624
  -5.000  -0.3072   0.02730   0.01975  -0.0763   1.0000   0.0644
  -4.750  -0.2778   0.02509   0.01707  -0.0769   1.0000   0.0662
  -4.500  -0.2489   0.02311   0.01470  -0.0772   1.0000   0.0702
  -4.250  -0.2230   0.02181   0.01336  -0.0774   1.0000   0.0809
  -4.000  -0.1957   0.02024   0.01179  -0.0775   1.0000   0.0957
  -3.500  -0.1425   0.01819   0.01017  -0.0787   1.0000   0.1611
  -3.250  -0.1129   0.01716   0.00954  -0.0800   1.0000   0.2279
  -3.000  -0.0892   0.01720   0.01056  -0.0797   1.0000   0.4687
  -2.750  -0.0506   0.01822   0.01145  -0.0814   0.9917   0.5199
  -2.500  -0.0089   0.01883   0.01191  -0.0840   0.9834   0.5541
  -2.250   0.0281   0.01926   0.01230  -0.0855   0.9734   0.5828
  -2.000   0.0631   0.01972   0.01280  -0.0863   0.9637   0.6131
  -1.750   0.1011   0.02009   0.01318  -0.0876   0.9555   0.6427
  -1.500   0.1341   0.02017   0.01323  -0.0885   0.9445   0.6603
  -1.250   0.1718   0.02018   0.01315  -0.0905   0.9350   0.6740
  -1.000   0.2154   0.02011   0.01297  -0.0937   0.9273   0.6864
  -0.750   0.2498   0.02006   0.01288  -0.0951   0.9165   0.6965
  -0.500   0.2891   0.01996   0.01274  -0.0973   0.9080   0.7060
  -0.250   0.3310   0.01982   0.01255  -0.1000   0.8999   0.7167
   0.000   0.3666   0.01975   0.01246  -0.1015   0.8898   0.7288
   0.250   0.4124   0.01941   0.01212  -0.1044   0.8838   0.7401
   0.500   0.4466   0.01917   0.01190  -0.1054   0.8721   0.7474
   0.750   0.4839   0.01890   0.01161  -0.1068   0.8612   0.7552
   1.000   0.5240   0.01845   0.01119  -0.1085   0.8530   0.7623
   1.250   0.5584   0.01823   0.01099  -0.1094   0.8422   0.7702
   1.500   0.5883   0.01806   0.01086  -0.1094   0.8305   0.7778
   1.750   0.6209   0.01788   0.01070  -0.1099   0.8196   0.7863
   2.000   0.6546   0.01755   0.01044  -0.1103   0.8099   0.7954
   2.250   0.6847   0.01731   0.01024  -0.1101   0.7977   0.8057
   2.500   0.7135   0.01702   0.01001  -0.1095   0.7834   0.8172
   2.750   0.7413   0.01670   0.00975  -0.1086   0.7686   0.8313
   3.000   0.7669   0.01640   0.00959  -0.1073   0.7538   0.8505
   3.250   0.7901   0.01610   0.00945  -0.1056   0.7392   0.8863
   3.500   0.8221   0.01598   0.00942  -0.1061   0.7229   1.0000
   3.750   0.8545   0.01607   0.00951  -0.1071   0.7055   1.0000
   4.000   0.8859   0.01616   0.00960  -0.1076   0.6878   1.0000
   4.250   0.9162   0.01623   0.00963  -0.1076   0.6694   1.0000
   4.500   0.9443   0.01635   0.00973  -0.1072   0.6484   1.0000
   4.750   0.9716   0.01648   0.00986  -0.1066   0.6259   1.0000
   5.000   0.9975   0.01670   0.01007  -0.1058   0.6007   1.0000
   5.250   1.0229   0.01694   0.01029  -0.1048   0.5727   1.0000
   5.500   1.0471   0.01722   0.01051  -0.1036   0.5408   1.0000
   5.750   1.0700   0.01755   0.01079  -0.1022   0.5049   1.0000
   6.000   1.0918   0.01793   0.01110  -0.1007   0.4659   1.0000
   6.250   1.1131   0.01844   0.01152  -0.0993   0.4268   1.0000
   6.500   1.1338   0.01911   0.01202  -0.0979   0.3904   1.0000
   6.750   1.1525   0.01988   0.01260  -0.0963   0.3516   1.0000
   7.000   1.1687   0.02067   0.01325  -0.0946   0.3087   1.0000
   7.250   1.1856   0.02146   0.01397  -0.0931   0.2695   1.0000
   7.500   1.2025   0.02231   0.01480  -0.0915   0.2312   1.0000
   7.750   1.2108   0.02394   0.01601  -0.0891   0.1478   1.0000
   8.000   1.2098   0.02721   0.01847  -0.0853   0.0777   1.0000
   8.250   1.2178   0.02942   0.02063  -0.0825   0.0652   1.0000
   8.500   1.2276   0.03159   0.02278  -0.0800   0.0584   1.0000
   8.750   1.2409   0.03341   0.02462  -0.0782   0.0524   1.0000
   9.000   1.2586   0.03605   0.02726  -0.0769   0.0486   1.0000
   9.250   1.2824   0.03840   0.02979  -0.0759   0.0462   1.0000
   9.500   1.3072   0.04114   0.03274  -0.0753   0.0444   1.0000
   9.750   1.3281   0.04396   0.03577  -0.0743   0.0426   1.0000
  10.000   1.3464   0.04706   0.03897  -0.0736   0.0404   1.0000
  10.250   1.3621   0.05254   0.04470  -0.0730   0.0390   1.0000
  10.500   1.3681   0.05612   0.04869  -0.0709   0.0388   1.0000
  10.750   1.3704   0.06034   0.05331  -0.0687   0.0389   1.0000
  11.000   1.3695   0.06464   0.05800  -0.0666   0.0391   1.0000
  11.250   1.3627   0.06756   0.06125  -0.0636   0.0393   1.0000
  11.500   1.3492   0.07024   0.06429  -0.0603   0.0397   1.0000
  11.750   1.3311   0.07338   0.06776  -0.0576   0.0401   1.0000
  12.000   1.3070   0.07750   0.07220  -0.0561   0.0407   1.0000
  12.250   1.2751   0.08290   0.07798  -0.0563   0.0414   1.0000
  12.500   1.2408   0.08969   0.08510  -0.0587   0.0420   1.0000
  12.750   1.2067   0.09781   0.09350  -0.0630   0.0427   1.0000
  13.000   1.1712   0.10761   0.10353  -0.0695   0.0434   1.0000
  13.250   1.1323   0.12010   0.11620  -0.0788   0.0444   1.0000
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