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WORTMANN FX 60-126 AIRFOIL (fx60126-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 60-126 AIRFOIL (fx60126-il)
Reynolds number: 200,000
Max Cl/Cd: 79.72 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx60126-il-200000.txt
Download as CSV file: xf-fx60126-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 60-126 AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3581   0.09764   0.09411  -0.0439   1.0000   0.0631
  -9.750  -0.4799   0.06403   0.06049  -0.0644   1.0000   0.0327
  -9.500  -0.5083   0.05967   0.05615  -0.0655   1.0000   0.0325
  -9.250  -0.5433   0.05769   0.05420  -0.0629   1.0000   0.0326
  -9.000  -0.5766   0.05546   0.05197  -0.0615   1.0000   0.0326
  -8.750  -0.5972   0.05217   0.04858  -0.0623   1.0000   0.0322
  -8.500  -0.6230   0.04101   0.03616  -0.0713   0.9974   0.0277
  -8.250  -0.5933   0.03637   0.03120  -0.0758   0.9938   0.0270
  -8.000  -0.5629   0.03225   0.02662  -0.0798   0.9892   0.0268
  -7.750  -0.5276   0.02901   0.02295  -0.0835   0.9852   0.0266
  -7.500  -0.4897   0.02652   0.02007  -0.0867   0.9822   0.0269
  -7.250  -0.4575   0.02476   0.01799  -0.0883   0.9770   0.0274
  -7.000  -0.4234   0.02278   0.01596  -0.0904   0.9734   0.0284
  -6.750  -0.3844   0.02177   0.01494  -0.0932   0.9705   0.0311
  -6.500  -0.3517   0.02080   0.01384  -0.0945   0.9653   0.0332
  -6.250  -0.3162   0.01927   0.01232  -0.0967   0.9606   0.0358
  -6.000  -0.2743   0.01816   0.01113  -0.0998   0.9572   0.0413
  -5.750  -0.2320   0.01649   0.00962  -0.1037   0.9541   0.0644
  -5.500  -0.1998   0.01550   0.00878  -0.1053   0.9475   0.1073
  -5.250  -0.1594   0.01461   0.00814  -0.1085   0.9438   0.1612
  -5.000  -0.1163   0.01381   0.00773  -0.1123   0.9413   0.2529
  -4.750  -0.0807   0.01354   0.00756  -0.1140   0.9363   0.3065
  -4.500  -0.0455   0.01340   0.00743  -0.1153   0.9305   0.3406
  -4.250  -0.0047   0.01325   0.00723  -0.1176   0.9267   0.3693
  -4.000   0.0298   0.01317   0.00711  -0.1185   0.9205   0.3908
  -3.750   0.0634   0.01312   0.00697  -0.1193   0.9137   0.4116
  -3.500   0.1007   0.01301   0.00685  -0.1206   0.9095   0.4311
  -3.250   0.1279   0.01303   0.00684  -0.1202   0.9004   0.4472
  -3.000   0.1616   0.01292   0.00669  -0.1208   0.8950   0.4619
  -2.750   0.1896   0.01290   0.00663  -0.1205   0.8864   0.4742
  -2.500   0.2207   0.01276   0.00648  -0.1206   0.8796   0.4855
  -2.250   0.2481   0.01272   0.00644  -0.1200   0.8698   0.4982
  -2.000   0.2786   0.01260   0.00627  -0.1198   0.8624   0.5112
  -1.750   0.3054   0.01258   0.00618  -0.1193   0.8514   0.5231
  -1.500   0.3335   0.01248   0.00611  -0.1188   0.8426   0.5320
  -1.250   0.3617   0.01239   0.00597  -0.1184   0.8330   0.5421
  -1.000   0.3891   0.01236   0.00592  -0.1180   0.8224   0.5521
  -0.750   0.4174   0.01226   0.00580  -0.1176   0.8129   0.5613
  -0.500   0.4452   0.01219   0.00567  -0.1172   0.8012   0.5717
  -0.250   0.4721   0.01212   0.00562  -0.1166   0.7887   0.5802
   0.000   0.4999   0.01206   0.00551  -0.1162   0.7768   0.5894
   0.250   0.5279   0.01200   0.00542  -0.1158   0.7653   0.5986
   0.500   0.5555   0.01195   0.00535  -0.1155   0.7531   0.6076
   0.750   0.5831   0.01194   0.00530  -0.1152   0.7397   0.6184
   1.000   0.6101   0.01191   0.00530  -0.1147   0.7264   0.6278
   1.250   0.6375   0.01191   0.00528  -0.1143   0.7131   0.6381
   1.500   0.6650   0.01193   0.00525  -0.1140   0.6988   0.6496
   1.750   0.6916   0.01191   0.00525  -0.1134   0.6831   0.6594
   2.000   0.7183   0.01192   0.00523  -0.1129   0.6665   0.6700
   2.250   0.7451   0.01197   0.00523  -0.1124   0.6498   0.6818
   2.500   0.7715   0.01202   0.00528  -0.1119   0.6337   0.6939
   2.750   0.7978   0.01208   0.00536  -0.1114   0.6190   0.7067
   3.000   0.8240   0.01218   0.00546  -0.1109   0.6052   0.7208
   3.250   0.8501   0.01228   0.00559  -0.1104   0.5916   0.7367
   3.500   0.8759   0.01239   0.00572  -0.1098   0.5777   0.7546
   3.750   0.9013   0.01249   0.00585  -0.1092   0.5631   0.7746
   4.000   0.9253   0.01256   0.00597  -0.1082   0.5475   0.7969
   4.250   0.9481   0.01260   0.00610  -0.1070   0.5315   0.8280
   4.500   0.9657   0.01249   0.00614  -0.1045   0.5164   0.8964
   4.750   0.9941   0.01262   0.00625  -0.1047   0.4990   1.0000
   5.000   1.0216   0.01290   0.00647  -0.1048   0.4829   1.0000
   5.250   1.0482   0.01319   0.00671  -0.1047   0.4668   1.0000
   5.500   1.0741   0.01349   0.00697  -0.1044   0.4502   1.0000
   5.750   1.0993   0.01379   0.00725  -0.1040   0.4321   1.0000
   6.000   1.1236   0.01413   0.00753  -0.1034   0.4130   1.0000
   6.250   1.1473   0.01453   0.00785  -0.1027   0.3936   1.0000
   6.500   1.1709   0.01489   0.00821  -0.1020   0.3722   1.0000
   6.750   1.1934   0.01534   0.00859  -0.1012   0.3510   1.0000
   7.000   1.2151   0.01585   0.00903  -0.1003   0.3285   1.0000
   7.250   1.2360   0.01639   0.00951  -0.0993   0.3039   1.0000
   7.500   1.2557   0.01702   0.01006  -0.0981   0.2791   1.0000
   7.750   1.2740   0.01774   0.01067  -0.0968   0.2520   1.0000
   8.000   1.2903   0.01859   0.01135  -0.0952   0.2265   1.0000
   8.250   1.3074   0.01939   0.01209  -0.0937   0.2025   1.0000
   8.500   1.3224   0.02031   0.01289  -0.0920   0.1838   1.0000
   8.750   1.3367   0.02127   0.01377  -0.0902   0.1683   1.0000
   9.000   1.3510   0.02217   0.01465  -0.0884   0.1545   1.0000
   9.250   1.3630   0.02308   0.01554  -0.0862   0.1428   1.0000
   9.500   1.3733   0.02411   0.01656  -0.0839   0.1328   1.0000
   9.750   1.3800   0.02546   0.01781  -0.0813   0.1242   1.0000
  10.000   1.3929   0.02637   0.01884  -0.0795   0.1159   1.0000
  10.250   1.4008   0.02772   0.02016  -0.0773   0.1096   1.0000
  10.500   1.4124   0.02878   0.02131  -0.0755   0.1035   1.0000
  10.750   1.4191   0.03037   0.02282  -0.0735   0.0984   1.0000
  11.000   1.4302   0.03159   0.02418  -0.0719   0.0937   1.0000
  11.250   1.4388   0.03304   0.02568  -0.0702   0.0893   1.0000
  11.500   1.4478   0.03489   0.02748  -0.0687   0.0850   1.0000
  11.750   1.4573   0.03629   0.02908  -0.0672   0.0814   1.0000
  12.000   1.4662   0.03785   0.03072  -0.0659   0.0781   1.0000
  12.250   1.4752   0.03959   0.03246  -0.0646   0.0753   1.0000
  12.500   1.4876   0.04146   0.03438  -0.0635   0.0727   1.0000
  12.750   1.4965   0.04320   0.03630  -0.0624   0.0707   1.0000
  13.000   1.5052   0.04500   0.03826  -0.0613   0.0686   1.0000
  13.250   1.5131   0.04683   0.04017  -0.0604   0.0666   1.0000
  13.500   1.5213   0.04869   0.04205  -0.0596   0.0646   1.0000
  13.750   1.5298   0.05100   0.04443  -0.0588   0.0623   1.0000
  14.000   1.5299   0.05342   0.04708  -0.0581   0.0607   1.0000
  14.250   1.5297   0.05598   0.04982  -0.0576   0.0587   1.0000
  14.500   1.5305   0.05852   0.05246  -0.0574   0.0568   1.0000
  14.750   1.5326   0.06104   0.05501  -0.0573   0.0549   1.0000
  15.000   1.5385   0.06399   0.05799  -0.0569   0.0524   1.0000
  15.250   1.5326   0.06743   0.06169  -0.0573   0.0515   1.0000
  15.500   1.5273   0.07109   0.06557  -0.0579   0.0502   1.0000
  15.750   1.5217   0.07502   0.06970  -0.0588   0.0489   1.0000
  16.000   1.5170   0.07898   0.07383  -0.0599   0.0475   1.0000
  16.250   1.5138   0.08284   0.07780  -0.0612   0.0461   1.0000
  16.500   1.5131   0.08635   0.08136  -0.0624   0.0447   1.0000
  16.750   1.5125   0.09012   0.08514  -0.0630   0.0428   1.0000
  17.000   1.5011   0.09566   0.09094  -0.0656   0.0422   1.0000
  17.250   1.4890   0.10156   0.09709  -0.0686   0.0412   1.0000
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