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WORTMANN FX 60-126/1 AIRFOIL (fx601261-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX 60-126/1 AIRFOIL (fx601261-il)
Reynolds number: 50,000
Max Cl/Cd: 39.41 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx601261-il-50000-n5.txt
Download as CSV file: xf-fx601261-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3255   0.10505   0.09793  -0.0442   1.0000   0.0363
  -9.500  -0.3276   0.10108   0.09405  -0.0452   1.0000   0.0356
  -9.250  -0.3316   0.09685   0.08993  -0.0465   1.0000   0.0347
  -8.750  -0.3580   0.08461   0.07796  -0.0514   1.0000   0.0324
  -8.500  -0.3667   0.08086   0.07432  -0.0518   1.0000   0.0322
  -8.250  -0.3794   0.07731   0.07090  -0.0519   1.0000   0.0319
  -8.000  -0.3986   0.07406   0.06778  -0.0513   1.0000   0.0316
  -7.750  -0.4218   0.07107   0.06491  -0.0504   1.0000   0.0313
  -7.500  -0.4432   0.06730   0.06118  -0.0515   1.0000   0.0310
  -7.250  -0.4610   0.06306   0.05690  -0.0541   1.0000   0.0307
  -7.000  -0.4721   0.05885   0.05253  -0.0565   1.0000   0.0303
  -6.750  -0.4748   0.05460   0.04803  -0.0590   1.0000   0.0300
  -6.500  -0.4525   0.04914   0.04204  -0.0657   0.9947   0.0297
  -6.250  -0.4209   0.04457   0.03689  -0.0714   0.9878   0.0296
  -6.000  -0.3876   0.04105   0.03282  -0.0755   0.9815   0.0296
  -5.750  -0.3536   0.03834   0.02967  -0.0785   0.9750   0.0298
  -5.500  -0.3207   0.03623   0.02720  -0.0805   0.9685   0.0301
  -5.250  -0.2873   0.03453   0.02520  -0.0822   0.9620   0.0309
  -5.000  -0.2549   0.03320   0.02359  -0.0836   0.9552   0.0321
  -4.750  -0.2212   0.03187   0.02211  -0.0856   0.9483   0.0342
  -4.500  -0.1870   0.03073   0.02078  -0.0877   0.9415   0.0368
  -4.250  -0.1510   0.02968   0.01945  -0.0899   0.9342   0.0398
  -4.000  -0.1124   0.02840   0.01807  -0.0931   0.9276   0.0439
  -3.750  -0.0753   0.02727   0.01682  -0.0958   0.9200   0.0508
  -3.500  -0.0283   0.02512   0.01526  -0.1014   0.9154   0.1504
  -3.250   0.0034   0.02459   0.01574  -0.1032   0.9064   0.3545
  -3.000   0.0409   0.02525   0.01644  -0.1042   0.9002   0.4364
  -2.750   0.0643   0.02605   0.01728  -0.1024   0.8900   0.4832
  -2.500   0.1037   0.02611   0.01711  -0.1040   0.8846   0.5089
  -2.250   0.1307   0.02614   0.01698  -0.1038   0.8746   0.5249
  -2.000   0.1707   0.02598   0.01659  -0.1056   0.8689   0.5415
  -1.750   0.1980   0.02598   0.01643  -0.1056   0.8583   0.5561
  -1.500   0.2345   0.02584   0.01612  -0.1068   0.8513   0.5720
  -1.250   0.2640   0.02582   0.01595  -0.1071   0.8413   0.5861
  -1.000   0.2957   0.02575   0.01576  -0.1076   0.8328   0.5989
  -0.750   0.3277   0.02567   0.01558  -0.1082   0.8243   0.6114
  -0.500   0.3561   0.02569   0.01552  -0.1083   0.8148   0.6245
  -0.250   0.3903   0.02557   0.01531  -0.1091   0.8072   0.6386
   0.000   0.4164   0.02564   0.01532  -0.1088   0.7963   0.6521
   0.250   0.4522   0.02543   0.01505  -0.1097   0.7891   0.6666
   0.500   0.4776   0.02551   0.01510  -0.1093   0.7774   0.6801
   0.750   0.5042   0.02554   0.01512  -0.1089   0.7670   0.6940
   1.000   0.5369   0.02536   0.01494  -0.1092   0.7591   0.7093
   1.250   0.5596   0.02551   0.01512  -0.1083   0.7475   0.7251
   1.500   0.5863   0.02551   0.01516  -0.1078   0.7380   0.7431
   1.750   0.6141   0.02537   0.01508  -0.1072   0.7288   0.7628
   2.000   0.6358   0.02541   0.01522  -0.1059   0.7169   0.7852
   2.250   0.6593   0.02529   0.01520  -0.1046   0.7063   0.8127
   2.500   0.6851   0.02497   0.01498  -0.1034   0.6970   0.8525
   2.750   0.7095   0.02491   0.01505  -0.1027   0.6846   1.0000
   3.000   0.7423   0.02518   0.01527  -0.1040   0.6736   1.0000
   3.250   0.7801   0.02515   0.01515  -0.1056   0.6651   1.0000
   3.500   0.8072   0.02552   0.01549  -0.1057   0.6521   1.0000
   3.750   0.8351   0.02580   0.01576  -0.1057   0.6392   1.0000
   4.000   0.8637   0.02600   0.01594  -0.1057   0.6268   1.0000
   4.250   0.8939   0.02613   0.01604  -0.1058   0.6151   1.0000
   4.500   0.9243   0.02623   0.01616  -0.1059   0.6035   1.0000
   4.750   0.9494   0.02659   0.01655  -0.1053   0.5896   1.0000
   5.000   0.9749   0.02688   0.01687  -0.1048   0.5754   1.0000
   5.250   1.0006   0.02712   0.01715  -0.1041   0.5606   1.0000
   5.500   1.0260   0.02735   0.01741  -0.1034   0.5452   1.0000
   5.750   1.0507   0.02763   0.01773  -0.1026   0.5296   1.0000
   6.000   1.0747   0.02791   0.01804  -0.1016   0.5130   1.0000
   6.250   1.0985   0.02817   0.01831  -0.1006   0.4958   1.0000
   6.500   1.1216   0.02846   0.01861  -0.0995   0.4781   1.0000
   6.750   1.1405   0.02899   0.01922  -0.0980   0.4592   1.0000
   7.000   1.1593   0.02955   0.01984  -0.0966   0.4402   1.0000
   7.250   1.1783   0.03006   0.02038  -0.0951   0.4210   1.0000
   7.500   1.1972   0.03058   0.02091  -0.0936   0.4017   1.0000
   7.750   1.2125   0.03134   0.02173  -0.0918   0.3817   1.0000
   8.000   1.2269   0.03215   0.02258  -0.0899   0.3616   1.0000
   8.250   1.2412   0.03298   0.02342  -0.0880   0.3421   1.0000
   8.500   1.2536   0.03393   0.02436  -0.0860   0.3228   1.0000
   8.750   1.2621   0.03505   0.02553  -0.0837   0.3035   1.0000
   9.000   1.2705   0.03623   0.02671  -0.0814   0.2855   1.0000
   9.250   1.2777   0.03757   0.02804  -0.0792   0.2679   1.0000
   9.500   1.2842   0.03903   0.02953  -0.0771   0.2516   1.0000
   9.750   1.2905   0.04059   0.03109  -0.0751   0.2370   1.0000
  10.000   1.2970   0.04228   0.03281  -0.0734   0.2235   1.0000
  10.250   1.3028   0.04409   0.03465  -0.0718   0.2108   1.0000
  10.500   1.3087   0.04597   0.03656  -0.0703   0.1995   1.0000
  10.750   1.3150   0.04787   0.03848  -0.0690   0.1894   1.0000
  11.000   1.3203   0.05001   0.04077  -0.0678   0.1794   1.0000
  11.250   1.3255   0.05213   0.04292  -0.0667   0.1705   1.0000
  11.500   1.3287   0.05450   0.04539  -0.0657   0.1616   1.0000
  11.750   1.3311   0.05705   0.04809  -0.0649   0.1535   1.0000
  12.000   1.3340   0.05949   0.05057  -0.0641   0.1462   1.0000
  12.250   1.3354   0.06237   0.05365  -0.0636   0.1395   1.0000
  12.500   1.3399   0.06489   0.05624  -0.0631   0.1336   1.0000
  12.750   1.3457   0.06754   0.05905  -0.0626   0.1286   1.0000
  13.000   1.3462   0.07092   0.06271  -0.0625   0.1238   1.0000
  13.250   1.3520   0.07360   0.06550  -0.0621   0.1194   1.0000
  13.500   1.3577   0.07648   0.06849  -0.0618   0.1155   1.0000
  13.750   1.3485   0.08135   0.07372  -0.0626   0.1123   1.0000
  14.000   1.3410   0.08609   0.07873  -0.0634   0.1094   1.0000
  14.250   1.3386   0.09016   0.08296  -0.0641   0.1066   1.0000
  14.500   1.3486   0.09251   0.08533  -0.0639   0.1037   1.0000
  14.750   1.3216   0.10054   0.09372  -0.0671   0.1024   1.0000
  15.000   1.2866   0.11069   0.10418  -0.0723   0.1015   1.0000
  15.250   1.2314   0.12633   0.12009  -0.0816   0.1011   1.0000
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