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FX 78-K-140 A/20 (fx78k140a20-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX 78-K-140 A/20 (fx78k140a20-il)
Reynolds number: 200,000
Max Cl/Cd: 54.64 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx78k140a20-il-200000.txt
Download as CSV file: xf-fx78k140a20-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 78-K-140 A/20                                
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.1015   0.10816   0.10380  -0.1150   0.8168   0.0401
 -11.250  -0.1018   0.10539   0.10108  -0.1175   0.8157   0.0404
 -11.000  -0.1009   0.10228   0.09800  -0.1196   0.8146   0.0406
 -10.750  -0.0983   0.09908   0.09483  -0.1213   0.8133   0.0407
 -10.500  -0.0968   0.09329   0.08908  -0.1212   0.8122   0.0417
 -10.250  -0.0837   0.09075   0.08651  -0.1201   0.8109   0.0430
 -10.000  -0.0786   0.08807   0.08383  -0.1206   0.8098   0.0438
  -9.750  -0.0743   0.08558   0.08136  -0.1210   0.8088   0.0453
  -9.500  -0.0735   0.08286   0.07867  -0.1219   0.8077   0.0457
  -9.250  -0.0751   0.07984   0.07571  -0.1227   0.8065   0.0471
  -9.000  -0.0775   0.07691   0.07284  -0.1238   0.8052   0.0477
  -8.750  -0.0877   0.07320   0.06921  -0.1257   0.8036   0.0499
  -8.500  -0.1053   0.06938   0.06545  -0.1282   0.8013   0.0512
  -8.250  -0.1177   0.06680   0.06290  -0.1275   0.7996   0.0511
  -8.000  -0.1488   0.06514   0.06110  -0.1249   0.7979   0.0527
  -7.750  -0.1614   0.06394   0.05970  -0.1224   0.7964   0.0531
  -7.500  -0.1707   0.06225   0.05783  -0.1196   0.7944   0.0534
  -7.250  -0.1794   0.05669   0.05228  -0.1182   0.7925   0.0545
  -7.000  -0.1718   0.05386   0.04950  -0.1172   0.7909   0.0555
  -6.750  -0.1646   0.05184   0.04745  -0.1157   0.7893   0.0570
  -6.500  -0.1589   0.04996   0.04548  -0.1138   0.7877   0.0592
  -6.250  -0.1530   0.04791   0.04323  -0.1116   0.7857   0.0614
  -6.000  -0.1572   0.04072   0.03519  -0.1060   0.7842   0.0380
  -5.750  -0.1598   0.03572   0.02948  -0.1010   0.7822   0.0318
  -5.500  -0.1484   0.03532   0.02907  -0.0994   0.7798   0.0339
  -5.250  -0.1374   0.03380   0.02725  -0.0969   0.7771   0.0344
  -5.000  -0.1221   0.03243   0.02556  -0.0948   0.7749   0.0363
  -4.750  -0.1033   0.03084   0.02360  -0.0930   0.7733   0.0369
  -4.500  -0.0803   0.02958   0.02201  -0.0917   0.7720   0.0391
  -4.250  -0.0555   0.02833   0.02055  -0.0911   0.7708   0.0435
  -4.000  -0.0534   0.02854   0.02079  -0.0878   0.7663   0.0463
  -3.750  -0.0424   0.02840   0.02057  -0.0853   0.7634   0.0498
  -3.500  -0.0241   0.02788   0.01996  -0.0838   0.7611   0.0562
  -3.250   0.0004   0.02745   0.01949  -0.0832   0.7592   0.0656
  -3.000   0.0255   0.02684   0.01889  -0.0825   0.7578   0.0786
  -2.750   0.0500   0.02639   0.01846  -0.0818   0.7567   0.0971
  -2.500   0.0190   0.02793   0.02001  -0.0737   0.7485   0.0954
  -2.250   0.0375   0.02762   0.01981  -0.0723   0.7462   0.1240
  -2.000   0.0561   0.02691   0.01960  -0.0708   0.7447   0.2211
  -1.750   0.0348   0.02749   0.02056  -0.0634   0.7384   0.3097
  -1.500   0.0174   0.02700   0.02107  -0.0559   0.7336   0.5517
  -1.250   0.0158   0.02700   0.02206  -0.0476   0.7314   0.8730
  -1.000   0.0509   0.02720   0.02218  -0.0465   0.7303   0.9304
  -0.750   0.4528   0.02619   0.02035  -0.1143   0.7435   0.9905
  -0.500   0.5035   0.02661   0.02072  -0.1209   0.7400   1.0000
  -0.250   0.5031   0.02746   0.02156  -0.1172   0.7344   1.0000
   0.000   0.5219   0.02763   0.02167  -0.1159   0.7319   1.0000
   0.250   0.5452   0.02767   0.02165  -0.1152   0.7303   1.0000
   0.500   0.5716   0.02765   0.02156  -0.1149   0.7291   1.0000
   0.750   0.5403   0.02942   0.02339  -0.1069   0.7187   1.0000
   1.000   0.5661   0.02938   0.02330  -0.1064   0.7170   1.0000
   1.250   0.5945   0.02929   0.02316  -0.1064   0.7158   1.0000
   1.500   0.5541   0.03111   0.02502  -0.0967   0.7048   1.0000
   1.750   0.5826   0.03103   0.02492  -0.0967   0.7032   1.0000
   2.000   0.6145   0.03084   0.02470  -0.0971   0.7021   1.0000
   2.250   0.6474   0.03064   0.02447  -0.0977   0.7012   1.0000
   2.500   0.6015   0.03222   0.02609  -0.0868   0.6892   1.0000
   2.750   0.6367   0.03199   0.02584  -0.0878   0.6882   1.0000
   3.000   0.5775   0.03332   0.02717  -0.0743   0.6760   1.0000
   3.250   0.5407   0.03436   0.02820  -0.0647   0.6657   1.0000
   3.500   0.5670   0.03421   0.02805  -0.0642   0.6633   1.0000
   3.750   0.5994   0.03394   0.02778  -0.0646   0.6619   1.0000
   4.000   0.6343   0.03366   0.02753  -0.0654   0.6610   1.0000
   4.250   0.6098   0.03480   0.02866  -0.0584   0.6495   1.0000
   4.500   0.6427   0.03453   0.02842  -0.0589   0.6482   1.0000
   4.750   0.6367   0.03573   0.02963  -0.0552   0.6381   1.0000
   5.000   0.6667   0.03559   0.02954  -0.0555   0.6360   1.0000
   5.250   0.7005   0.03524   0.02924  -0.0561   0.6347   1.0000
   5.500   0.7362   0.03476   0.02881  -0.0569   0.6337   1.0000
   5.750   0.7342   0.03601   0.03009  -0.0540   0.6226   1.0000
   6.000   0.7678   0.03559   0.02976  -0.0546   0.6212   1.0000
   6.250   0.8040   0.03499   0.02924  -0.0553   0.6202   1.0000
   6.500   0.8409   0.03433   0.02869  -0.0561   0.6195   1.0000
   6.750   0.8397   0.03572   0.03012  -0.0537   0.6077   1.0000
   7.000   0.8663   0.03560   0.03013  -0.0536   0.6039   1.0000
   7.250   0.9135   0.03414   0.02882  -0.0551   0.6059   1.0000
   8.000   1.0686   0.02392   0.01910  -0.0574   0.5907   1.0000
   8.250   1.0870   0.02270   0.01791  -0.0554   0.5587   1.0000
   8.500   1.1124   0.02036   0.01452  -0.0516   0.4122   1.0000
   8.750   1.0870   0.02335   0.01695  -0.0465   0.3327   1.0000
   9.000   1.0627   0.02662   0.01969  -0.0421   0.2535   1.0000
   9.250   1.0324   0.03051   0.02287  -0.0375   0.1516   1.0000
   9.500   1.0103   0.03405   0.02576  -0.0339   0.0618   1.0000
   9.750   1.0028   0.03677   0.02825  -0.0313   0.0347   1.0000
  10.000   1.0078   0.03866   0.03024  -0.0298   0.0307   1.0000
  10.250   1.0119   0.04068   0.03237  -0.0285   0.0256   1.0000
  10.500   1.0119   0.04309   0.03486  -0.0269   0.0235   1.0000
  10.750   1.0137   0.04537   0.03724  -0.0255   0.0222   1.0000
  11.000   1.0191   0.04733   0.03929  -0.0242   0.0216   1.0000
  11.250   1.0265   0.04910   0.04114  -0.0229   0.0212   1.0000
  11.500   1.0354   0.05069   0.04279  -0.0213   0.0204   1.0000
  11.750   1.0487   0.05188   0.04404  -0.0198   0.0196   1.0000
  12.000   1.0679   0.05265   0.04485  -0.0180   0.0192   1.0000
  12.250   1.0955   0.05313   0.04543  -0.0163   0.0193   1.0000
  12.500   1.1247   0.05412   0.04661  -0.0151   0.0188   1.0000
  12.750   1.1612   0.05578   0.04855  -0.0140   0.0198   1.0000
  13.000   1.1657   0.05775   0.05046  -0.0135   0.0166   1.0000
  13.250   1.1883   0.06112   0.05443  -0.0117   0.0190   1.0000
  13.500   1.1981   0.06565   0.05935  -0.0100   0.0208   1.0000
  13.750   1.0077   0.05787   0.05182   0.0066   0.0184   1.0000
  14.000   1.0047   0.06177   0.05607   0.0083   0.0190   1.0000
  14.250   0.9917   0.06540   0.06000   0.0100   0.0200   1.0000
  14.500   0.9702   0.06903   0.06391   0.0115   0.0204   1.0000
  14.750   0.9543   0.07281   0.06793   0.0121   0.0212   1.0000
  15.000   0.9352   0.07714   0.07249   0.0123   0.0218   1.0000
  15.250   0.9147   0.08193   0.07776   0.0125   0.0265   1.0000
  15.500   0.8847   0.08748   0.08358   0.0111   0.0277   1.0000
  15.750   0.8588   0.09282   0.08913   0.0092   0.0283   1.0000
  16.000   0.8327   0.09853   0.09503   0.0065   0.0286   1.0000
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