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FX 63-143 AIRFOIL (fx63143-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX 63-143 AIRFOIL (fx63143-il)
Reynolds number: 50,000
Max Cl/Cd: 23.98 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx63143-il-50000-n5.txt
Download as CSV file: xf-fx63143-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 63-143 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3677   0.10202   0.09526  -0.0432   1.0000   0.0397
 -10.000  -0.3780   0.09547   0.08880  -0.0472   1.0000   0.0372
  -9.750  -0.3792   0.09131   0.08473  -0.0488   1.0000   0.0367
  -9.500  -0.3837   0.08648   0.07998  -0.0512   1.0000   0.0361
  -9.250  -0.3938   0.08126   0.07483  -0.0541   1.0000   0.0355
  -9.000  -0.4102   0.07662   0.07025  -0.0558   1.0000   0.0346
  -8.750  -0.4455   0.07196   0.06556  -0.0554   1.0000   0.0332
  -8.500  -0.4634   0.06940   0.06305  -0.0530   1.0000   0.0331
  -8.250  -0.4767   0.06694   0.06062  -0.0505   1.0000   0.0328
  -8.000  -0.4936   0.06467   0.05836  -0.0473   1.0000   0.0327
  -7.750  -0.5114   0.06317   0.05689  -0.0432   1.0000   0.0324
  -7.500  -0.4989   0.05834   0.05170  -0.0464   0.9801   0.0323
  -7.250  -0.4841   0.05387   0.04680  -0.0485   0.9583   0.0322
  -7.000  -0.4646   0.04972   0.04216  -0.0503   0.9409   0.0321
  -6.750  -0.4412   0.04590   0.03781  -0.0518   0.9261   0.0321
  -6.500  -0.4126   0.04222   0.03354  -0.0534   0.9138   0.0323
  -6.250  -0.3804   0.03889   0.02958  -0.0549   0.9022   0.0329
  -6.000  -0.3482   0.03629   0.02653  -0.0561   0.8897   0.0339
  -5.750  -0.3115   0.03397   0.02384  -0.0576   0.8792   0.0355
  -5.500  -0.2735   0.03181   0.02130  -0.0589   0.8685   0.0382
  -5.250  -0.2392   0.03027   0.01958  -0.0599   0.8567   0.0429
  -5.000  -0.2044   0.02895   0.01815  -0.0611   0.8462   0.0486
  -4.750  -0.1746   0.02799   0.01703  -0.0615   0.8337   0.0558
  -4.500  -0.1476   0.02718   0.01587  -0.0612   0.8211   0.0650
  -4.250  -0.1219   0.02623   0.01484  -0.0610   0.8100   0.0753
  -4.000  -0.0981   0.02549   0.01408  -0.0605   0.7986   0.0908
  -3.750  -0.0779   0.02460   0.01337  -0.0596   0.7874   0.1223
  -3.500  -0.0637   0.02290   0.01270  -0.0581   0.7788   0.3062
  -3.250  -0.0555   0.02193   0.01294  -0.0540   0.7685   0.5450
  -3.000  -0.0044   0.02257   0.01401  -0.0539   0.7622   0.7366
  -2.750   0.0226   0.02310   0.01430  -0.0527   0.7527   0.7788
  -2.500   0.0545   0.02373   0.01463  -0.0519   0.7454   0.8221
  -2.250   0.0878   0.02449   0.01514  -0.0515   0.7366   0.8631
  -2.000   0.1441   0.02495   0.01525  -0.0555   0.7296   0.8984
  -1.750   0.1923   0.02506   0.01508  -0.0592   0.7221   0.9198
  -1.500   0.2381   0.02502   0.01477  -0.0628   0.7149   0.9381
  -1.250   0.2872   0.02487   0.01436  -0.0672   0.7087   0.9557
  -1.000   0.3314   0.02472   0.01404  -0.0711   0.7002   0.9701
  -0.750   0.3771   0.02440   0.01347  -0.0751   0.6934   0.9806
  -0.500   0.4153   0.02427   0.01323  -0.0782   0.6843   0.9905
  -0.250   0.4560   0.02405   0.01282  -0.0814   0.6774   0.9992
   0.000   0.4744   0.02426   0.01298  -0.0805   0.6698   1.0000
   0.250   0.4929   0.02445   0.01308  -0.0795   0.6633   1.0000
   0.500   0.5135   0.02460   0.01311  -0.0786   0.6583   1.0000
   0.750   0.5277   0.02504   0.01357  -0.0771   0.6512   1.0000
   1.000   0.5461   0.02529   0.01376  -0.0759   0.6455   1.0000
   1.250   0.5653   0.02555   0.01395  -0.0748   0.6404   1.0000
   1.500   0.5781   0.02607   0.01451  -0.0729   0.6331   1.0000
   1.750   0.5967   0.02637   0.01475  -0.0717   0.6278   1.0000
   2.000   0.6135   0.02676   0.01511  -0.0702   0.6223   1.0000
   2.250   0.6253   0.02737   0.01576  -0.0681   0.6155   1.0000
   2.500   0.6446   0.02764   0.01598  -0.0668   0.6102   1.0000
   2.750   0.6574   0.02819   0.01658  -0.0647   0.6036   1.0000
   3.000   0.6698   0.02872   0.01713  -0.0626   0.5965   1.0000
   3.250   0.6920   0.02886   0.01722  -0.0615   0.5917   1.0000
   3.500   0.6949   0.02982   0.01827  -0.0582   0.5837   1.0000
   3.750   0.7092   0.03035   0.01883  -0.0563   0.5784   1.0000
   4.000   0.7310   0.03062   0.01912  -0.0553   0.5747   1.0000
   4.250   0.7252   0.03198   0.02060  -0.0510   0.5668   1.0000
   4.500   0.7388   0.03256   0.02122  -0.0490   0.5618   1.0000
   4.750   0.7629   0.03273   0.02140  -0.0482   0.5582   1.0000
   5.000   0.7483   0.03434   0.02312  -0.0428   0.5490   1.0000
   5.250   0.7700   0.03448   0.02331  -0.0415   0.5438   1.0000
   5.500   0.7655   0.03565   0.02455  -0.0373   0.5359   1.0000
   5.750   0.7723   0.03639   0.02535  -0.0344   0.5292   1.0000
   6.000   0.8018   0.03629   0.02532  -0.0341   0.5252   1.0000
   6.250   0.7713   0.03865   0.02775  -0.0274   0.5146   1.0000
   6.500   0.7963   0.03876   0.02794  -0.0267   0.5100   1.0000
   6.750   0.7728   0.04120   0.03043  -0.0217   0.4998   1.0000
   7.000   0.7942   0.04155   0.03088  -0.0208   0.4944   1.0000
   7.250   0.7754   0.04404   0.03341  -0.0169   0.4844   1.0000
   7.500   0.7982   0.04417   0.03365  -0.0160   0.4778   1.0000
   7.750   0.7863   0.04674   0.03628  -0.0136   0.4671   1.0000
   8.000   0.8175   0.04596   0.03563  -0.0128   0.4601   1.0000
   8.250   0.8039   0.04902   0.03875  -0.0112   0.4477   1.0000
   8.500   0.8529   0.04628   0.03617  -0.0103   0.4418   1.0000
   8.750   0.8354   0.04984   0.03980  -0.0090   0.4286   1.0000
   9.000   0.8931   0.04612   0.03629  -0.0080   0.4240   1.0000
   9.250   0.8688   0.05052   0.04076  -0.0070   0.4101   1.0000
   9.750   0.8885   0.05306   0.04359  -0.0056   0.3919   1.0000
  10.250   0.9081   0.05578   0.04662  -0.0044   0.3743   1.0000
  10.750   0.9005   0.06178   0.05287  -0.0042   0.3505   1.0000
  11.500   0.9343   0.06527   0.05690  -0.0028   0.3214   1.0000
  11.750   0.9428   0.06676   0.05858  -0.0025   0.3105   1.0000
  12.250   0.9556   0.07027   0.06245  -0.0020   0.2864   1.0000
  12.500   0.9752   0.06998   0.06238  -0.0011   0.2740   1.0000
  12.750   0.9730   0.07300   0.06555  -0.0014   0.2585   1.0000
  13.000   0.9807   0.07445   0.06717  -0.0011   0.2420   1.0000
  13.250   1.0101   0.07198   0.06467   0.0009   0.2171   1.0000
  13.500   0.9975   0.07665   0.06943  -0.0002   0.1948   1.0000
  13.750   1.0048   0.07766   0.07009   0.0003   0.1681   1.0000
  14.000   0.9973   0.08182   0.07424  -0.0007   0.1474   1.0000
  14.250   0.9957   0.08488   0.07704  -0.0013   0.1325   1.0000
  14.500   0.9923   0.08854   0.08058  -0.0021   0.1193   1.0000
  14.750   0.9875   0.09281   0.08493  -0.0035   0.1062   1.0000
  15.000   0.9858   0.09645   0.08848  -0.0046   0.0975   1.0000
  15.250   0.9869   0.09962   0.09155  -0.0053   0.0903   1.0000
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