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FX 61-147 AIRFOIL (fx61147-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: FX 61-147 AIRFOIL (fx61147-il)
Reynolds number: 500,000
Max Cl/Cd: 98.7 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx61147-il-500000-n5.txt
Download as CSV file: xf-fx61147-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 61-147 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.6120   0.04387   0.04100  -0.0772   0.9947   0.0039
 -10.500  -0.6310   0.03645   0.03309  -0.0826   0.9869   0.0039
 -10.250  -0.6362   0.03143   0.02763  -0.0851   0.9769   0.0039
 -10.000  -0.6263   0.02783   0.02363  -0.0866   0.9684   0.0039
  -9.500  -0.5892   0.02329   0.01850  -0.0882   0.9555   0.0040
  -9.250  -0.5645   0.02159   0.01658  -0.0892   0.9505   0.0041
  -9.000  -0.5417   0.02025   0.01504  -0.0895   0.9438   0.0042
  -8.750  -0.5141   0.01885   0.01349  -0.0907   0.9383   0.0044
  -8.500  -0.4822   0.01789   0.01244  -0.0925   0.9336   0.0047
  -8.250  -0.4511   0.01708   0.01152  -0.0939   0.9261   0.0049
  -8.000  -0.4122   0.01620   0.01054  -0.0970   0.9209   0.0053
  -7.750  -0.3753   0.01537   0.00960  -0.0996   0.9126   0.0058
  -7.500  -0.3301   0.01451   0.00862  -0.1039   0.9057   0.0065
  -7.250  -0.2862   0.01393   0.00798  -0.1080   0.8959   0.0073
  -7.000  -0.2453   0.01342   0.00735  -0.1112   0.8839   0.0086
  -6.750  -0.2076   0.01294   0.00678  -0.1139   0.8682   0.0098
  -6.500  -0.1728   0.01261   0.00634  -0.1157   0.8498   0.0111
  -6.250  -0.1424   0.01235   0.00596  -0.1166   0.8293   0.0126
  -6.000  -0.1147   0.01212   0.00565  -0.1170   0.8079   0.0147
  -5.750  -0.0880   0.01196   0.00536  -0.1170   0.7873   0.0164
  -5.500  -0.0627   0.01163   0.00492  -0.1168   0.7665   0.0185
  -5.250  -0.0373   0.01142   0.00459  -0.1166   0.7462   0.0202
  -5.000  -0.0117   0.01124   0.00427  -0.1164   0.7270   0.0217
  -4.750   0.0141   0.01103   0.00394  -0.1162   0.7085   0.0246
  -4.500   0.0401   0.01086   0.00370  -0.1160   0.6903   0.0295
  -4.250   0.0664   0.01069   0.00346  -0.1160   0.6733   0.0389
  -4.000   0.0933   0.01051   0.00324  -0.1161   0.6582   0.0544
  -3.750   0.1209   0.01024   0.00302  -0.1164   0.6449   0.0877
  -3.500   0.1503   0.00963   0.00272  -0.1176   0.6325   0.1934
  -3.250   0.1825   0.00879   0.00238  -0.1198   0.6205   0.3578
  -3.000   0.2149   0.00823   0.00223  -0.1216   0.6088   0.4988
  -2.750   0.2445   0.00813   0.00227  -0.1221   0.5983   0.5623
  -2.500   0.2729   0.00819   0.00234  -0.1223   0.5891   0.5949
  -2.000   0.3292   0.00839   0.00242  -0.1223   0.5705   0.6264
  -1.750   0.3570   0.00849   0.00245  -0.1223   0.5617   0.6321
  -1.500   0.3852   0.00857   0.00246  -0.1224   0.5530   0.6377
  -1.250   0.4135   0.00866   0.00246  -0.1225   0.5447   0.6428
  -1.000   0.4411   0.00875   0.00250  -0.1225   0.5360   0.6464
  -0.750   0.4693   0.00884   0.00253  -0.1226   0.5283   0.6506
  -0.500   0.4974   0.00894   0.00255  -0.1227   0.5210   0.6551
  -0.250   0.5255   0.00902   0.00259  -0.1228   0.5142   0.6585
   0.000   0.5532   0.00912   0.00265  -0.1228   0.5071   0.6616
   0.250   0.5812   0.00921   0.00270  -0.1228   0.5010   0.6649
   0.500   0.6094   0.00930   0.00275  -0.1230   0.4949   0.6684
   0.750   0.6374   0.00941   0.00280  -0.1231   0.4893   0.6717
   1.000   0.6653   0.00948   0.00288  -0.1232   0.4833   0.6739
   1.250   0.6927   0.00959   0.00296  -0.1231   0.4771   0.6764
   1.500   0.7204   0.00970   0.00305  -0.1232   0.4712   0.6792
   1.750   0.7482   0.00980   0.00313  -0.1233   0.4646   0.6822
   2.000   0.7757   0.00993   0.00321  -0.1233   0.4584   0.6852
   2.250   0.8035   0.01002   0.00331  -0.1234   0.4521   0.6876
   2.500   0.8304   0.01014   0.00343  -0.1233   0.4462   0.6896
   2.750   0.8579   0.01025   0.00354  -0.1233   0.4407   0.6917
   3.000   0.8852   0.01036   0.00367  -0.1233   0.4351   0.6940
   3.250   0.9121   0.01051   0.00380  -0.1232   0.4297   0.6965
   3.500   0.9398   0.01062   0.00392  -0.1233   0.4239   0.6989
   3.750   0.9669   0.01076   0.00405  -0.1233   0.4183   0.7013
   4.000   0.9936   0.01089   0.00421  -0.1232   0.4135   0.7031
   4.250   1.0205   0.01101   0.00437  -0.1232   0.4081   0.7050
   4.500   1.0468   0.01117   0.00454  -0.1230   0.4025   0.7069
   4.750   1.0735   0.01131   0.00472  -0.1229   0.3969   0.7090
   5.000   1.1001   0.01146   0.00490  -0.1228   0.3909   0.7113
   5.250   1.1260   0.01164   0.00509  -0.1226   0.3857   0.7136
   5.500   1.1528   0.01179   0.00529  -0.1225   0.3791   0.7157
   5.750   1.1778   0.01199   0.00550  -0.1222   0.3705   0.7175
   6.000   1.2026   0.01219   0.00571  -0.1218   0.3592   0.7193
   6.250   1.2269   0.01243   0.00595  -0.1213   0.3463   0.7211
   6.500   1.2511   0.01268   0.00622  -0.1208   0.3346   0.7231
   6.750   1.2747   0.01296   0.00649  -0.1202   0.3218   0.7253
   7.000   1.2956   0.01340   0.00683  -0.1192   0.2977   0.7274
   7.250   1.3145   0.01397   0.00725  -0.1179   0.2662   0.7296
   7.500   1.3327   0.01459   0.00772  -0.1165   0.2362   0.7315
   7.750   1.3498   0.01524   0.00827  -0.1149   0.2087   0.7333
   8.000   1.3607   0.01623   0.00902  -0.1124   0.1648   0.7350
   8.250   1.3665   0.01734   0.00990  -0.1089   0.1237   0.7368
   8.500   1.3724   0.01845   0.01082  -0.1056   0.0915   0.7390
   8.750   1.3809   0.01941   0.01168  -0.1027   0.0682   0.7412
   9.000   1.3905   0.02030   0.01251  -0.1001   0.0538   0.7434
   9.250   1.4005   0.02117   0.01335  -0.0976   0.0420   0.7454
   9.500   1.4089   0.02212   0.01431  -0.0950   0.0317   0.7471
   9.750   1.4174   0.02308   0.01528  -0.0926   0.0249   0.7489
  10.000   1.4248   0.02414   0.01637  -0.0901   0.0194   0.7509
  10.250   1.4336   0.02517   0.01745  -0.0879   0.0156   0.7532
  10.500   1.4400   0.02639   0.01872  -0.0857   0.0116   0.7554
  10.750   1.4431   0.02791   0.02025  -0.0833   0.0065   0.7575
  11.000   1.4450   0.02961   0.02200  -0.0811   0.0042   0.7595
  11.250   1.4483   0.03132   0.02379  -0.0792   0.0035   0.7613
  11.500   1.4523   0.03307   0.02565  -0.0777   0.0031   0.7632
  11.750   1.4558   0.03499   0.02768  -0.0763   0.0029   0.7653
  12.000   1.4582   0.03712   0.02994  -0.0752   0.0027   0.7677
  12.250   1.4593   0.03950   0.03244  -0.0742   0.0025   0.7700
  12.500   1.4600   0.04207   0.03513  -0.0735   0.0024   0.7723
  12.750   1.4597   0.04489   0.03806  -0.0730   0.0023   0.7744
  13.000   1.4582   0.04796   0.04127  -0.0728   0.0022   0.7762
  13.250   1.4577   0.05106   0.04449  -0.0727   0.0021   0.7781
  13.500   1.4569   0.05429   0.04785  -0.0729   0.0021   0.7801
  13.750   1.4554   0.05772   0.05140  -0.0732   0.0021   0.7823
  14.000   1.4533   0.06135   0.05516  -0.0736   0.0020   0.7846
  14.250   1.4505   0.06518   0.05911  -0.0743   0.0020   0.7870
  14.500   1.4475   0.06915   0.06321  -0.0751   0.0020   0.7892
  14.750   1.4438   0.07331   0.06750  -0.0761   0.0019   0.7913
  15.000   1.4397   0.07764   0.07196  -0.0772   0.0019   0.7934
  15.250   1.4354   0.08212   0.07657  -0.0785   0.0018   0.7955
  15.500   1.4307   0.08676   0.08136  -0.0800   0.0018   0.7977
  15.750   1.4257   0.09155   0.08628  -0.0816   0.0018   0.7999
  16.000   1.4203   0.09651   0.09136  -0.0834   0.0017   0.8021
  16.500   1.4102   0.10654   0.10165  -0.0873   0.0017   0.8066
  16.750   1.4047   0.11174   0.10698  -0.0895   0.0016   0.8090
  17.000   1.3996   0.11697   0.11233  -0.0918   0.0016   0.8117
  17.250   1.3942   0.12231   0.11780  -0.0942   0.0016   0.8148
  17.500   1.3889   0.12764   0.12325  -0.0968   0.0016   0.8179
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