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FX 63-145 AIRFOIL (fx63145-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX 63-145 AIRFOIL (fx63145-il)
Reynolds number: 200,000
Max Cl/Cd: 75.57 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx63145-il-200000.txt
Download as CSV file: xf-fx63145-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 63-145 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2853   0.09693   0.09387  -0.0420   1.0000   0.0442
  -9.000  -0.3055   0.09089   0.08794  -0.0476   1.0000   0.0452
  -8.750  -0.3249   0.08446   0.08159  -0.0529   0.9997   0.0453
  -8.500  -0.2842   0.08431   0.08144  -0.0489   0.9953   0.0471
  -8.250  -0.2683   0.08009   0.07724  -0.0531   0.9791   0.0490
  -8.000  -0.2670   0.07218   0.06935  -0.0631   0.9476   0.0515
  -7.500  -0.2237   0.05364   0.05041  -0.0978   0.8816   0.0568
  -7.250  -0.1964   0.04614   0.04228  -0.1127   0.8403   0.0629
  -6.750  -0.1504   0.03949   0.03488  -0.1198   0.7727   0.0730
  -6.500  -0.1349   0.03689   0.03177  -0.1213   0.7477   0.0806
  -6.250  -0.1153   0.03501   0.02959  -0.1219   0.7283   0.0897
  -6.000  -0.0949   0.03307   0.02744  -0.1223   0.7103   0.0996
  -5.750  -0.0736   0.03093   0.02513  -0.1227   0.6943   0.1102
  -5.500  -0.0317   0.02492   0.01751  -0.1201   0.6842   0.0375
  -5.250  -0.0049   0.02245   0.01469  -0.1192   0.6718   0.0306
  -5.000   0.0214   0.02065   0.01256  -0.1184   0.6596   0.0277
  -4.750   0.0481   0.01964   0.01126  -0.1176   0.6478   0.0262
  -4.500   0.0731   0.01850   0.01005  -0.1168   0.6347   0.0256
  -4.250   0.0985   0.01753   0.00903  -0.1161   0.6233   0.0251
  -4.000   0.1246   0.01672   0.00814  -0.1157   0.6132   0.0248
  -3.750   0.1522   0.01596   0.00733  -0.1159   0.6037   0.0249
  -3.500   0.1811   0.01533   0.00659  -0.1163   0.5951   0.0254
  -3.250   0.2108   0.01484   0.00596  -0.1168   0.5860   0.0265
  -3.000   0.2402   0.01451   0.00552  -0.1172   0.5777   0.0292
  -2.750   0.2701   0.01420   0.00508  -0.1176   0.5695   0.0366
  -2.500   0.3026   0.01337   0.00446  -0.1190   0.5624   0.1405
  -2.250   0.3371   0.01212   0.00424  -0.1218   0.5553   0.4239
  -2.000   0.3659   0.01207   0.00428  -0.1219   0.5492   0.4899
  -1.750   0.3943   0.01212   0.00437  -0.1219   0.5433   0.5284
  -1.500   0.4229   0.01225   0.00446  -0.1219   0.5374   0.5642
  -1.250   0.4510   0.01238   0.00450  -0.1217   0.5325   0.5832
  -1.000   0.4790   0.01251   0.00462  -0.1216   0.5277   0.6011
  -0.750   0.5064   0.01269   0.00482  -0.1212   0.5224   0.6233
  -0.500   0.5349   0.01279   0.00482  -0.1212   0.5170   0.6341
  -0.250   0.5624   0.01286   0.00488  -0.1210   0.5117   0.6410
   0.000   0.5910   0.01293   0.00490  -0.1211   0.5058   0.6501
   0.250   0.6179   0.01301   0.00497  -0.1208   0.5002   0.6573
   0.500   0.6463   0.01311   0.00501  -0.1208   0.4942   0.6663
   0.750   0.6730   0.01318   0.00507  -0.1205   0.4874   0.6732
   1.000   0.7006   0.01329   0.00510  -0.1204   0.4807   0.6814
   1.250   0.7279   0.01336   0.00517  -0.1203   0.4732   0.6877
   1.500   0.7547   0.01347   0.00523  -0.1200   0.4664   0.6945
   1.750   0.7825   0.01354   0.00534  -0.1200   0.4590   0.7027
   2.000   0.8087   0.01365   0.00549  -0.1196   0.4515   0.7134
   2.250   0.8348   0.01375   0.00565  -0.1191   0.4450   0.7244
   2.500   0.8623   0.01386   0.00577  -0.1190   0.4378   0.7352
   2.750   0.8882   0.01394   0.00589  -0.1186   0.4311   0.7418
   3.000   0.9155   0.01405   0.00600  -0.1185   0.4248   0.7493
   3.250   0.9412   0.01416   0.00611  -0.1181   0.4189   0.7558
   3.500   0.9674   0.01428   0.00626  -0.1178   0.4130   0.7638
   3.750   0.9930   0.01442   0.00641  -0.1174   0.4061   0.7720
   4.000   1.0184   0.01457   0.00661  -0.1170   0.3982   0.7808
   4.250   1.0438   0.01471   0.00681  -0.1166   0.3865   0.7896
   4.500   1.0693   0.01485   0.00700  -0.1162   0.3713   0.7997
   4.750   1.0921   0.01505   0.00719  -0.1153   0.3605   0.8095
   5.000   1.1156   0.01526   0.00742  -0.1145   0.3527   0.8211
   5.250   1.1380   0.01548   0.00766  -0.1135   0.3454   0.8332
   5.500   1.1597   0.01568   0.00792  -0.1124   0.3389   0.8461
   5.750   1.1825   0.01581   0.00819  -0.1114   0.3305   0.8602
   6.000   1.2039   0.01596   0.00844  -0.1102   0.3198   0.8758
   6.250   1.2220   0.01617   0.00869  -0.1084   0.3042   0.8944
   6.500   1.2357   0.01642   0.00894  -0.1059   0.2933   0.9209
   6.750   1.2537   0.01664   0.00918  -0.1043   0.2850   1.0000
   7.000   1.2838   0.01709   0.00965  -0.1055   0.2771   1.0000
   7.250   1.3121   0.01752   0.01013  -0.1062   0.2664   1.0000
   7.500   1.3370   0.01805   0.01065  -0.1064   0.2449   1.0000
   7.750   1.3528   0.01903   0.01141  -0.1051   0.2290   1.0000
   8.500   1.4063   0.02125   0.01353  -0.1019   0.1835   1.0000
   8.750   1.4157   0.02222   0.01443  -0.0995   0.1766   1.0000
   9.000   1.4289   0.02301   0.01528  -0.0977   0.1698   1.0000
   9.250   1.4389   0.02395   0.01626  -0.0956   0.1657   1.0000
   9.500   1.4608   0.02429   0.01678  -0.0949   0.1553   1.0000
   9.750   1.4682   0.02540   0.01783  -0.0927   0.1420   1.0000
  10.000   1.4695   0.02692   0.01923  -0.0901   0.1362   1.0000
  10.250   1.4714   0.02850   0.02084  -0.0878   0.1313   1.0000
  10.500   1.4717   0.03034   0.02273  -0.0857   0.1275   1.0000
  10.750   1.4694   0.03256   0.02498  -0.0839   0.1248   1.0000
  11.000   1.4831   0.03366   0.02626  -0.0833   0.1185   1.0000
  11.250   1.5045   0.03415   0.02696  -0.0830   0.1055   1.0000
  11.500   1.5051   0.03646   0.02922  -0.0821   0.1000   1.0000
  11.750   1.5046   0.03903   0.03175  -0.0814   0.0961   1.0000
  12.000   1.5014   0.04202   0.03475  -0.0809   0.0935   1.0000
  12.250   1.4974   0.04524   0.03802  -0.0806   0.0914   1.0000
  12.500   1.4961   0.04828   0.04116  -0.0804   0.0894   1.0000
  12.750   1.4974   0.05110   0.04413  -0.0804   0.0873   1.0000
  13.000   1.4955   0.05435   0.04750  -0.0805   0.0851   1.0000
  13.250   1.4907   0.05801   0.05126  -0.0807   0.0833   1.0000
  13.500   1.4925   0.06095   0.05434  -0.0809   0.0812   1.0000
  13.750   1.5168   0.06116   0.05489  -0.0807   0.0736   1.0000
  14.000   1.5126   0.06496   0.05864  -0.0813   0.0587   1.0000
  14.250   1.5035   0.06952   0.06314  -0.0822   0.0551   1.0000
  14.500   1.5004   0.07341   0.06716  -0.0829   0.0527   1.0000
  14.750   1.4966   0.07751   0.07142  -0.0838   0.0503   1.0000
  15.000   1.4895   0.08220   0.07625  -0.0850   0.0480   1.0000
  15.250   1.4823   0.08704   0.08121  -0.0863   0.0459   1.0000
  15.500   1.4930   0.08917   0.08360  -0.0868   0.0369   1.0000
  15.750   1.4840   0.09441   0.08888  -0.0885   0.0300   1.0000
  16.000   1.4751   0.09982   0.09432  -0.0903   0.0251   1.0000
  16.250   1.4643   0.10566   0.10021  -0.0926   0.0213   1.0000
  16.500   1.4557   0.11128   0.10595  -0.0948   0.0183   1.0000
  16.750   1.4448   0.11743   0.11221  -0.0975   0.0160   1.0000
  17.000   1.4324   0.12399   0.11889  -0.1005   0.0146   1.0000
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