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FX 63-147 AIRFOIL (fx63147-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: FX 63-147 AIRFOIL (fx63147-il)
Reynolds number: 1,000,000
Max Cl/Cd: 97.27 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx63147-il-1000000-n5.txt
Download as CSV file: xf-fx63147-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 63-147 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3892   0.05499   0.05317  -0.0950   0.9835   0.0037
  -9.750  -0.4177   0.04833   0.04634  -0.0969   0.9758   0.0037
  -9.500  -0.4453   0.04308   0.04089  -0.0951   0.9642   0.0037
  -9.250  -0.4851   0.03387   0.03122  -0.0918   0.9462   0.0040
  -9.000  -0.4862   0.02846   0.02533  -0.0911   0.9339   0.0042
  -8.750  -0.4630   0.02562   0.02214  -0.0928   0.9238   0.0043
  -8.500  -0.4249   0.02297   0.01900  -0.0973   0.9133   0.0046
  -8.250  -0.3764   0.02025   0.01589  -0.1038   0.9003   0.0046
  -8.000  -0.3338   0.01814   0.01341  -0.1084   0.8722   0.0047
  -7.750  -0.3098   0.01710   0.01207  -0.1084   0.8357   0.0048
  -7.500  -0.2899   0.01640   0.01112  -0.1073   0.8053   0.0048
  -7.250  -0.2705   0.01559   0.01014  -0.1061   0.7826   0.0049
  -7.000  -0.2499   0.01496   0.00936  -0.1051   0.7634   0.0050
  -6.750  -0.2287   0.01443   0.00872  -0.1042   0.7454   0.0052
  -6.500  -0.2072   0.01392   0.00809  -0.1033   0.7294   0.0054
  -6.250  -0.1855   0.01340   0.00745  -0.1023   0.7146   0.0054
  -6.000  -0.1636   0.01291   0.00684  -0.1014   0.7008   0.0053
  -5.750  -0.1412   0.01249   0.00630  -0.1006   0.6877   0.0052
  -5.500  -0.1184   0.01209   0.00581  -0.0999   0.6749   0.0051
  -5.250  -0.0950   0.01173   0.00536  -0.0992   0.6625   0.0051
  -5.000  -0.0712   0.01141   0.00496  -0.0987   0.6503   0.0050
  -4.750  -0.0471   0.01111   0.00458  -0.0983   0.6388   0.0050
  -4.250   0.0031   0.01060   0.00393  -0.0977   0.6156   0.0049
  -4.000   0.0289   0.01037   0.00364  -0.0975   0.6057   0.0049
  -3.750   0.0554   0.01017   0.00338  -0.0975   0.5970   0.0049
  -3.500   0.0825   0.00996   0.00313  -0.0976   0.5898   0.0049
  -3.250   0.1098   0.00979   0.00291  -0.0977   0.5820   0.0050
  -3.000   0.1375   0.00964   0.00272  -0.0979   0.5747   0.0050
  -2.750   0.1653   0.00952   0.00255  -0.0980   0.5667   0.0050
  -2.500   0.1936   0.00942   0.00240  -0.0983   0.5596   0.0051
  -2.250   0.2218   0.00933   0.00227  -0.0986   0.5527   0.0053
  -2.000   0.2502   0.00926   0.00216  -0.0989   0.5465   0.0054
  -1.750   0.2787   0.00920   0.00207  -0.0992   0.5388   0.0058
  -1.500   0.3071   0.00917   0.00199  -0.0995   0.5318   0.0063
  -1.250   0.3361   0.00911   0.00193  -0.0999   0.5248   0.0132
  -0.750   0.3943   0.00900   0.00186  -0.1009   0.5130   0.0422
  -0.500   0.4238   0.00893   0.00183  -0.1014   0.5074   0.0672
  -0.250   0.4542   0.00879   0.00181  -0.1024   0.5021   0.1236
   0.000   0.5235   0.00713   0.00166  -0.1139   0.4959   0.6256
   0.250   0.5588   0.00707   0.00174  -0.1158   0.4898   0.6827
   0.500   0.5902   0.00710   0.00183  -0.1167   0.4838   0.7138
   0.750   0.6197   0.00717   0.00190  -0.1172   0.4768   0.7252
   1.000   0.6488   0.00727   0.00198  -0.1176   0.4700   0.7350
   1.250   0.6783   0.00735   0.00205  -0.1180   0.4633   0.7460
   1.500   0.7062   0.00749   0.00216  -0.1182   0.4501   0.7549
   1.750   0.7335   0.00774   0.00226  -0.1183   0.4220   0.7623
   2.000   0.7594   0.00799   0.00240  -0.1181   0.3967   0.7673
   2.250   0.7869   0.00819   0.00253  -0.1182   0.3807   0.7728
   2.500   0.8146   0.00841   0.00265  -0.1184   0.3617   0.7774
   2.750   0.8404   0.00864   0.00281  -0.1182   0.3431   0.7805
   3.000   0.8655   0.00898   0.00302  -0.1179   0.3150   0.7833
   3.250   0.8883   0.00953   0.00331  -0.1172   0.2675   0.7861
   3.500   0.9062   0.01051   0.00385  -0.1158   0.1845   0.7887
   3.750   0.9239   0.01149   0.00444  -0.1144   0.1052   0.7911
   4.000   0.9473   0.01196   0.00477  -0.1139   0.0784   0.7931
   4.250   0.9711   0.01231   0.00506  -0.1133   0.0611   0.7949
   4.500   0.9959   0.01257   0.00530  -0.1130   0.0536   0.7970
   4.750   1.0186   0.01301   0.00566  -0.1123   0.0338   0.7994
   5.000   1.0434   0.01329   0.00593  -0.1119   0.0292   0.8018
   5.250   1.0689   0.01352   0.00617  -0.1117   0.0270   0.8039
   5.500   1.0927   0.01387   0.00649  -0.1113   0.0165   0.8057
   5.750   1.1167   0.01420   0.00680  -0.1109   0.0143   0.8074
   6.000   1.1405   0.01448   0.00708  -0.1104   0.0130   0.8089
   6.250   1.1637   0.01476   0.00739  -0.1097   0.0126   0.8105
   6.500   1.1861   0.01507   0.00774  -0.1090   0.0120   0.8121
   6.750   1.2066   0.01543   0.00813  -0.1079   0.0111   0.8139
   7.000   1.2268   0.01580   0.00853  -0.1067   0.0103   0.8159
   7.250   1.2476   0.01618   0.00894  -0.1058   0.0099   0.8180
   7.500   1.2682   0.01658   0.00938  -0.1048   0.0095   0.8198
   7.750   1.2893   0.01695   0.00976  -0.1039   0.0094   0.8214
   8.000   1.3100   0.01734   0.01017  -0.1030   0.0092   0.8229
   8.250   1.3290   0.01774   0.01061  -0.1018   0.0089   0.8243
   8.500   1.3471   0.01816   0.01108  -0.1005   0.0085   0.8258
   8.750   1.3649   0.01862   0.01157  -0.0991   0.0080   0.8273
   9.000   1.3819   0.01911   0.01209  -0.0976   0.0075   0.8288
   9.250   1.3975   0.01967   0.01268  -0.0960   0.0067   0.8303
   9.500   1.4158   0.02014   0.01318  -0.0949   0.0059   0.8318
   9.750   1.4288   0.02088   0.01391  -0.0931   0.0025   0.8334
  10.000   1.4418   0.02167   0.01474  -0.0913   0.0020   0.8350
  10.250   1.4547   0.02248   0.01561  -0.0896   0.0019   0.8365
  10.500   1.4667   0.02339   0.01658  -0.0879   0.0017   0.8380
  10.750   1.4776   0.02437   0.01763  -0.0861   0.0016   0.8394
  11.000   1.4872   0.02545   0.01879  -0.0843   0.0016   0.8408
  11.250   1.4964   0.02664   0.02005  -0.0826   0.0015   0.8421
  11.500   1.5049   0.02793   0.02142  -0.0811   0.0014   0.8433
  11.750   1.5124   0.02937   0.02294  -0.0796   0.0014   0.8447
  12.000   1.5192   0.03097   0.02462  -0.0782   0.0013   0.8460
  12.250   1.5253   0.03271   0.02645  -0.0771   0.0013   0.8475
  12.500   1.5315   0.03454   0.02836  -0.0761   0.0013   0.8490
  12.750   1.5367   0.03652   0.03043  -0.0753   0.0012   0.8504
  13.000   1.5412   0.03867   0.03266  -0.0745   0.0012   0.8516
  13.250   1.5449   0.04098   0.03506  -0.0740   0.0012   0.8527
  13.500   1.5474   0.04345   0.03762  -0.0735   0.0012   0.8537
  13.750   1.5487   0.04609   0.04035  -0.0730   0.0011   0.8549
  14.000   1.5491   0.04890   0.04326  -0.0727   0.0011   0.8560
  14.250   1.5487   0.05185   0.04632  -0.0725   0.0011   0.8570
  14.500   1.5470   0.05499   0.04956  -0.0723   0.0011   0.8579
  14.750   1.5449   0.05829   0.05296  -0.0723   0.0010   0.8588
  15.000   1.5420   0.06170   0.05647  -0.0724   0.0010   0.8597
  15.250   1.5382   0.06534   0.06022  -0.0726   0.0010   0.8606
  15.500   1.5336   0.06907   0.06405  -0.0729   0.0010   0.8615
  15.750   1.5288   0.07294   0.06803  -0.0734   0.0010   0.8624
  16.000   1.5233   0.07696   0.07214  -0.0739   0.0010   0.8633
  16.250   1.5169   0.08118   0.07647  -0.0746   0.0009   0.8642
  16.500   1.5105   0.08541   0.08080  -0.0754   0.0009   0.8651
  16.750   1.5034   0.08980   0.08529  -0.0763   0.0009   0.8659
  17.000   1.4962   0.09431   0.08990  -0.0773   0.0009   0.8666
  17.250   1.4888   0.09890   0.09459  -0.0785   0.0009   0.8672
  17.500   1.4811   0.10356   0.09935  -0.0797   0.0009   0.8678
  17.750   1.4732   0.10832   0.10421  -0.0812   0.0009   0.8683
  18.000   1.4648   0.11318   0.10918  -0.0827   0.0008   0.8689
  18.250   1.4560   0.11822   0.11432  -0.0845   0.0008   0.8696
  18.500   1.4478   0.12310   0.11930  -0.0862   0.0008   0.8703
  18.750   1.4389   0.12831   0.12462  -0.0883   0.0008   0.8709
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