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FX 63-100 AIRFOIL (fx63100-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: FX 63-100 AIRFOIL (fx63100-il)
Reynolds number: 50,000
Max Cl/Cd: 42.96 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx63100-il-50000.txt
Download as CSV file: xf-fx63100-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 63-100 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3428   0.11451   0.10748  -0.0305   1.0000   0.2111
  -8.750  -0.3243   0.10951   0.10248  -0.0291   1.0000   0.2190
  -8.500  -0.3435   0.10982   0.10296  -0.0294   1.0000   0.2267
  -8.250  -0.3220   0.10474   0.09787  -0.0277   1.0000   0.2373
  -8.000  -0.3303   0.10313   0.09640  -0.0271   1.0000   0.2446
  -7.750  -0.3348   0.10174   0.09511  -0.0257   1.0000   0.2563
  -7.500  -0.3258   0.09849   0.09192  -0.0239   1.0000   0.2697
  -7.250  -0.3217   0.09581   0.08931  -0.0220   1.0000   0.2817
  -7.000  -0.3249   0.09386   0.08748  -0.0198   1.0000   0.2941
  -6.750  -0.3523   0.09455   0.08838  -0.0163   1.0000   0.3025
  -6.500  -0.3482   0.09188   0.08578  -0.0136   1.0000   0.3169
  -6.250  -0.3449   0.08926   0.08323  -0.0110   1.0000   0.3298
  -6.000  -0.3563   0.08787   0.08195  -0.0075   1.0000   0.3395
  -5.750  -0.3860   0.08863   0.08290  -0.0044   1.0000   0.3499
  -5.500  -0.3851   0.08620   0.08053  -0.0013   1.0000   0.3651
  -5.250  -0.3832   0.08373   0.07812   0.0017   1.0000   0.3795
  -5.000  -0.3908   0.08218   0.07667   0.0044   1.0000   0.3961
  -4.750  -0.4026   0.08110   0.07568   0.0063   1.0000   0.4134
  -4.250  -0.2976   0.04984   0.04330  -0.0633   1.0000   0.1849
  -4.000  -0.2162   0.03951   0.03158  -0.0817   1.0000   0.1549
  -3.750  -0.1735   0.03598   0.02744  -0.0867   1.0000   0.1570
  -3.500  -0.1328   0.03314   0.02398  -0.0905   1.0000   0.1586
  -3.250  -0.0948   0.03126   0.02141  -0.0933   1.0000   0.1658
  -3.000  -0.0671   0.02968   0.01977  -0.0939   1.0000   0.1733
  -2.750  -0.0385   0.02851   0.01833  -0.0945   1.0000   0.1837
  -2.500  -0.0122   0.02758   0.01736  -0.0946   1.0000   0.1990
  -2.250   0.0143   0.02677   0.01662  -0.0947   1.0000   0.2188
  -2.000   0.0438   0.02607   0.01612  -0.0955   1.0000   0.2605
  -1.750   0.0797   0.02482   0.01644  -0.0967   1.0000   0.4963
  -1.500   0.0815   0.02555   0.01761  -0.0898   1.0000   0.6594
  -1.250   0.0837   0.02601   0.01815  -0.0840   1.0000   0.7276
  -1.000   0.0862   0.02620   0.01837  -0.0786   1.0000   0.7829
  -0.750   0.0866   0.02612   0.01833  -0.0731   1.0000   0.8368
  -0.500   0.0816   0.02567   0.01800  -0.0668   1.0000   0.9064
  -0.250   0.0971   0.02546   0.01772  -0.0674   1.0000   1.0000
   0.000   0.1396   0.02634   0.01823  -0.0733   1.0000   1.0000
   0.250   0.1783   0.02733   0.01890  -0.0781   0.9984   1.0000
   0.500   0.2362   0.02877   0.01999  -0.0859   0.9858   1.0000
   0.750   0.2889   0.03006   0.02101  -0.0925   0.9732   1.0000
   1.000   0.3364   0.03121   0.02195  -0.0978   0.9603   1.0000
   1.250   0.3808   0.03229   0.02286  -0.1024   0.9470   1.0000
   1.500   0.4228   0.03331   0.02376  -0.1064   0.9335   1.0000
   1.750   0.4632   0.03431   0.02467  -0.1099   0.9196   1.0000
   2.000   0.5010   0.03531   0.02560  -0.1129   0.9056   1.0000
   2.250   0.5380   0.03629   0.02654  -0.1156   0.8912   1.0000
   2.500   0.5737   0.03728   0.02751  -0.1179   0.8767   1.0000
   2.750   0.6089   0.03825   0.02850  -0.1201   0.8619   1.0000
   3.000   0.6435   0.03921   0.02948  -0.1220   0.8471   1.0000
   3.250   0.6780   0.04013   0.03044  -0.1238   0.8319   1.0000
   3.500   0.7129   0.04098   0.03136  -0.1253   0.8162   1.0000
   3.750   0.7485   0.04171   0.03217  -0.1268   0.8000   1.0000
   4.000   0.7867   0.04221   0.03277  -0.1282   0.7833   1.0000
   4.250   0.8283   0.04241   0.03312  -0.1296   0.7664   1.0000
   4.500   0.8725   0.04230   0.03317  -0.1309   0.7497   1.0000
   4.750   0.9197   0.04182   0.03287  -0.1321   0.7334   1.0000
   5.000   0.9456   0.04234   0.03357  -0.1314   0.7140   1.0000
   5.250   0.9823   0.04215   0.03357  -0.1312   0.6951   1.0000
   5.500   1.0290   0.04105   0.03275  -0.1314   0.6770   1.0000
   5.750   1.0827   0.03909   0.03105  -0.1314   0.6587   1.0000
   6.000   1.1227   0.03769   0.02988  -0.1301   0.6349   1.0000
   6.250   1.1758   0.03439   0.02678  -0.1283   0.6047   1.0000
   6.500   1.2158   0.03223   0.02471  -0.1260   0.5699   1.0000
   6.750   1.2496   0.03084   0.02335  -0.1237   0.5316   1.0000
   7.000   1.2719   0.03014   0.02255  -0.1202   0.4837   1.0000
   7.250   1.2883   0.02999   0.02205  -0.1163   0.4264   1.0000
   7.500   1.2955   0.03093   0.02262  -0.1120   0.3639   1.0000
   7.750   1.3003   0.03264   0.02387  -0.1080   0.3018   1.0000
   8.000   1.3091   0.03494   0.02563  -0.1049   0.2498   1.0000
   8.250   1.3263   0.03756   0.02789  -0.1031   0.2115   1.0000
   8.500   1.3549   0.04043   0.03046  -0.1029   0.1858   1.0000
   8.750   1.3784   0.04309   0.03321  -0.1021   0.1688   1.0000
   9.000   1.4049   0.04599   0.03617  -0.1018   0.1566   1.0000
   9.250   1.4265   0.04901   0.03951  -0.1008   0.1482   1.0000
   9.500   1.4440   0.05235   0.04312  -0.0996   0.1411   1.0000
   9.750   1.4576   0.05564   0.04679  -0.0980   0.1352   1.0000
  10.000   1.4795   0.05974   0.05092  -0.0976   0.1303   1.0000
  10.250   1.4746   0.06371   0.05559  -0.0943   0.1280   1.0000
  10.500   1.4668   0.06791   0.06033  -0.0912   0.1257   1.0000
  10.750   1.4560   0.07230   0.06516  -0.0883   0.1241   1.0000
  11.000   1.4386   0.07701   0.07026  -0.0854   0.1238   1.0000
  11.250   1.4122   0.08170   0.07527  -0.0822   0.1244   1.0000
  11.500   1.3812   0.08699   0.08083  -0.0802   0.1253   1.0000
  11.750   1.3473   0.09326   0.08733  -0.0799   0.1267   1.0000
  12.000   1.3140   0.10060   0.09484  -0.0814   0.1282   1.0000
  12.250   1.2856   0.10871   0.10307  -0.0842   0.1296   1.0000
  12.500   1.2649   0.11708   0.11153  -0.0875   0.1306   1.0000
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