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WORTMANN FX 60-126/1 AIRFOIL (fx601261-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 60-126/1 AIRFOIL (fx601261-il)
Reynolds number: 50,000
Max Cl/Cd: 34.45 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx601261-il-50000.txt
Download as CSV file: xf-fx601261-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2823   0.10562   0.09919  -0.0295   1.0000   0.2444
  -8.000  -0.3073   0.10552   0.09932  -0.0291   1.0000   0.2499
  -7.750  -0.2989   0.10176   0.09562  -0.0280   1.0000   0.2513
  -7.500  -0.2999   0.09912   0.09310  -0.0266   1.0000   0.2524
  -7.250  -0.3087   0.09715   0.09126  -0.0247   1.0000   0.2527
  -7.000  -0.3705   0.09055   0.08488  -0.0289   1.0000   0.1559
  -6.750  -0.4157   0.08509   0.07961  -0.0323   1.0000   0.1295
  -6.500  -0.4376   0.07816   0.07275  -0.0376   1.0000   0.1154
  -6.250  -0.4570   0.06847   0.06296  -0.0476   1.0000   0.1047
  -6.000  -0.4544   0.06372   0.05811  -0.0498   1.0000   0.0994
  -5.750  -0.4424   0.05206   0.04526  -0.0644   1.0000   0.0886
  -5.500  -0.4248   0.04811   0.04115  -0.0658   1.0000   0.0868
  -5.250  -0.4013   0.04400   0.03663  -0.0684   1.0000   0.0849
  -5.000  -0.3739   0.04030   0.03239  -0.0709   1.0000   0.0833
  -4.750  -0.3459   0.03734   0.02892  -0.0725   1.0000   0.0828
  -4.500  -0.3196   0.03514   0.02631  -0.0732   1.0000   0.0834
  -4.250  -0.2945   0.03340   0.02426  -0.0731   1.0000   0.0853
  -4.000  -0.2706   0.03215   0.02267  -0.0727   1.0000   0.0886
  -3.750  -0.2490   0.03095   0.02160  -0.0722   1.0000   0.0950
  -3.500  -0.2256   0.03002   0.02056  -0.0719   1.0000   0.1045
  -3.250  -0.2006   0.02892   0.01959  -0.0722   1.0000   0.1211
  -3.000  -0.1603   0.02674   0.01921  -0.0757   1.0000   0.3753
  -2.750  -0.1537   0.02891   0.02154  -0.0711   1.0000   0.4613
  -2.500  -0.1498   0.03063   0.02341  -0.0657   1.0000   0.5070
  -2.250  -0.1526   0.03222   0.02525  -0.0583   1.0000   0.5459
  -2.000  -0.1449   0.03300   0.02600  -0.0542   1.0000   0.5834
  -1.750  -0.1336   0.03316   0.02610  -0.0514   1.0000   0.6060
  -1.500  -0.1004   0.03354   0.02627  -0.0529   0.9920   0.6349
  -1.250  -0.0621   0.03389   0.02638  -0.0555   0.9814   0.6626
  -1.000  -0.0240   0.03425   0.02653  -0.0582   0.9705   0.6902
  -0.750   0.0094   0.03449   0.02662  -0.0598   0.9595   0.7130
  -0.500   0.0443   0.03471   0.02665  -0.0622   0.9478   0.7358
  -0.250   0.0751   0.03493   0.02675  -0.0635   0.9358   0.7576
   0.000   0.1095   0.03523   0.02690  -0.0657   0.9239   0.7805
   0.250   0.1420   0.03550   0.02707  -0.0672   0.9123   0.8025
   0.500   0.1792   0.03582   0.02729  -0.0696   0.9009   0.8268
   0.750   0.2012   0.03601   0.02747  -0.0695   0.8887   0.8507
   1.000   0.2242   0.03623   0.02768  -0.0695   0.8766   0.8795
   1.250   0.2527   0.03642   0.02794  -0.0705   0.8647   0.9218
   1.500   0.3026   0.03699   0.02843  -0.0768   0.8501   1.0000
   1.750   0.3577   0.03793   0.02920  -0.0841   0.8363   1.0000
   2.000   0.4113   0.03885   0.02994  -0.0906   0.8227   1.0000
   2.250   0.4648   0.03968   0.03063  -0.0965   0.8099   1.0000
   2.500   0.4999   0.04072   0.03155  -0.0996   0.7960   1.0000
   2.750   0.5324   0.04178   0.03251  -0.1019   0.7823   1.0000
   3.000   0.5629   0.04286   0.03351  -0.1037   0.7687   1.0000
   3.250   0.5944   0.04383   0.03441  -0.1052   0.7546   1.0000
   3.500   0.6254   0.04475   0.03529  -0.1063   0.7404   1.0000
   3.750   0.6555   0.04565   0.03616  -0.1072   0.7264   1.0000
   4.000   0.6848   0.04657   0.03707  -0.1078   0.7126   1.0000
   4.250   0.7146   0.04745   0.03799  -0.1084   0.6993   1.0000
   4.500   0.7473   0.04814   0.03869  -0.1090   0.6862   1.0000
   4.750   0.7856   0.04835   0.03894  -0.1098   0.6729   1.0000
   5.000   0.8182   0.04862   0.03930  -0.1097   0.6579   1.0000
   5.250   0.8646   0.04791   0.03869  -0.1103   0.6446   1.0000
   5.500   0.8941   0.04823   0.03908  -0.1098   0.6299   1.0000
   5.750   0.9298   0.04798   0.03895  -0.1094   0.6152   1.0000
   6.000   0.9753   0.04665   0.03774  -0.1091   0.6001   1.0000
   6.250   1.0251   0.04470   0.03594  -0.1087   0.5848   1.0000
   6.500   1.0446   0.04517   0.03651  -0.1068   0.5662   1.0000
   6.750   1.0796   0.04426   0.03572  -0.1056   0.5479   1.0000
   7.000   1.1369   0.04136   0.03293  -0.1053   0.5287   1.0000
   7.250   1.1898   0.03898   0.03058  -0.1051   0.5078   1.0000
   7.500   1.2121   0.03922   0.03093  -0.1032   0.4853   1.0000
   7.750   1.2499   0.03833   0.03002  -0.1023   0.4613   1.0000
   8.000   1.2865   0.03745   0.02900  -0.1013   0.4343   1.0000
   8.250   1.3034   0.03802   0.02964  -0.0990   0.4078   1.0000
   8.500   1.3227   0.03856   0.03013  -0.0969   0.3813   1.0000
   8.750   1.3446   0.03903   0.03048  -0.0951   0.3557   1.0000
   9.000   1.3652   0.04005   0.03142  -0.0936   0.3328   1.0000
   9.250   1.3847   0.04152   0.03286  -0.0921   0.3130   1.0000
   9.500   1.3985   0.04339   0.03487  -0.0903   0.2954   1.0000
   9.750   1.4132   0.04515   0.03668  -0.0885   0.2786   1.0000
  10.000   1.4273   0.04669   0.03824  -0.0867   0.2619   1.0000
  10.250   1.4411   0.04818   0.03972  -0.0848   0.2460   1.0000
  10.500   1.4508   0.05014   0.04177  -0.0828   0.2327   1.0000
  10.750   1.4594   0.05228   0.04401  -0.0808   0.2207   1.0000
  11.000   1.4746   0.05463   0.04644  -0.0796   0.2100   1.0000
  11.250   1.4749   0.05760   0.04970  -0.0771   0.2023   1.0000
  11.500   1.4789   0.06084   0.05312  -0.0752   0.1956   1.0000
  11.750   1.4568   0.06474   0.05740  -0.0713   0.1924   1.0000
  12.000   1.4861   0.06754   0.06015  -0.0716   0.1836   1.0000
  12.250   1.4517   0.07198   0.06494  -0.0675   0.1829   1.0000
  12.500   1.4131   0.07743   0.07069  -0.0650   0.1828   1.0000
  12.750   1.3697   0.08437   0.07786  -0.0643   0.1832   1.0000
  13.000   1.3218   0.09322   0.08689  -0.0659   0.1841   1.0000
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