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FX 63-100 AIRFOIL (fx63100-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: FX 63-100 AIRFOIL (fx63100-il)
Reynolds number: 200,000
Max Cl/Cd: 90.01 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx63100-il-200000-n5.txt
Download as CSV file: xf-fx63100-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3464   0.09319   0.08964  -0.0394   1.0000   0.0178
  -8.750  -0.3513   0.08989   0.08640  -0.0395   1.0000   0.0179
  -8.500  -0.3583   0.08692   0.08349  -0.0389   1.0000   0.0178
  -8.250  -0.3608   0.08293   0.07957  -0.0407   0.9984   0.0178
  -8.000  -0.3502   0.07680   0.07345  -0.0478   0.9918   0.0177
  -7.750  -0.3410   0.06970   0.06638  -0.0565   0.9816   0.0177
  -7.500  -0.3268   0.05817   0.05485  -0.0733   0.9687   0.0177
  -7.250  -0.2925   0.02852   0.02358  -0.1155   0.9529   0.0182
  -7.000  -0.2579   0.02449   0.01889  -0.1204   0.9469   0.0200
  -6.750  -0.2228   0.02346   0.01773  -0.1229   0.9432   0.0212
  -6.500  -0.1883   0.02166   0.01560  -0.1254   0.9385   0.0228
  -6.250  -0.1535   0.01979   0.01334  -0.1277   0.9333   0.0247
  -6.000  -0.1165   0.01843   0.01174  -0.1302   0.9298   0.0273
  -5.750  -0.0795   0.01774   0.01097  -0.1325   0.9262   0.0299
  -5.500  -0.0457   0.01682   0.00987  -0.1339   0.9199   0.0327
  -5.250  -0.0087   0.01586   0.00874  -0.1360   0.9156   0.0362
  -5.000   0.0291   0.01509   0.00790  -0.1383   0.9118   0.0398
  -4.750   0.0626   0.01460   0.00732  -0.1396   0.9049   0.0439
  -4.500   0.0993   0.01403   0.00662  -0.1414   0.8997   0.0470
  -4.000   0.1696   0.01289   0.00540  -0.1447   0.8865   0.0554
  -3.750   0.2051   0.01249   0.00490  -0.1463   0.8802   0.0600
  -3.500   0.2375   0.01214   0.00454  -0.1474   0.8718   0.0674
  -3.250   0.2713   0.01183   0.00419  -0.1486   0.8647   0.0778
  -3.000   0.3024   0.01158   0.00392  -0.1493   0.8555   0.0930
  -2.750   0.3340   0.01133   0.00365  -0.1500   0.8457   0.1140
  -2.500   0.3659   0.01098   0.00339  -0.1510   0.8356   0.1583
  -2.250   0.3974   0.01040   0.00333  -0.1523   0.8249   0.3221
  -2.000   0.4275   0.01023   0.00329  -0.1527   0.8160   0.3928
  -1.750   0.4569   0.01008   0.00331  -0.1530   0.8071   0.4533
  -1.500   0.4854   0.01003   0.00340  -0.1530   0.7983   0.5076
  -1.250   0.5141   0.01005   0.00341  -0.1529   0.7900   0.5422
  -1.000   0.5421   0.01009   0.00346  -0.1527   0.7808   0.5711
  -0.750   0.5707   0.01014   0.00346  -0.1526   0.7727   0.5942
  -0.500   0.5982   0.01018   0.00351  -0.1524   0.7633   0.6148
  -0.250   0.6259   0.01023   0.00356  -0.1521   0.7548   0.6350
   0.000   0.6535   0.01028   0.00360  -0.1518   0.7457   0.6526
   0.250   0.6810   0.01033   0.00366  -0.1516   0.7365   0.6657
   0.750   0.7361   0.01047   0.00377  -0.1511   0.7177   0.6898
   1.000   0.7635   0.01054   0.00384  -0.1508   0.7084   0.7020
   1.250   0.7907   0.01061   0.00391  -0.1504   0.6984   0.7135
   1.500   0.8177   0.01069   0.00401  -0.1501   0.6877   0.7249
   1.750   0.8446   0.01077   0.00410  -0.1497   0.6759   0.7371
   2.000   0.8708   0.01087   0.00417  -0.1492   0.6600   0.7500
   2.250   0.8964   0.01097   0.00426  -0.1485   0.6417   0.7629
   2.500   0.9220   0.01108   0.00436  -0.1478   0.6250   0.7766
   2.750   0.9477   0.01119   0.00449  -0.1472   0.6103   0.7917
   3.000   0.9728   0.01131   0.00464  -0.1465   0.5952   0.8088
   3.250   0.9965   0.01142   0.00478  -0.1454   0.5791   0.8307
   3.500   1.0175   0.01151   0.00489  -0.1437   0.5597   0.8643
   3.750   1.0351   0.01150   0.00492  -0.1412   0.5353   1.0000
   4.000   1.0603   0.01184   0.00512  -0.1407   0.5040   1.0000
   4.250   1.0847   0.01225   0.00536  -0.1401   0.4719   1.0000
   4.750   1.1318   0.01321   0.00601  -0.1387   0.4070   1.0000
   5.000   1.1552   0.01371   0.00638  -0.1380   0.3753   1.0000
   5.250   1.1779   0.01427   0.00679  -0.1372   0.3385   1.0000
   5.500   1.1997   0.01490   0.00727  -0.1363   0.3000   1.0000
   5.750   1.2209   0.01561   0.00779  -0.1354   0.2617   1.0000
   6.000   1.2413   0.01639   0.00838  -0.1344   0.2259   1.0000
   6.250   1.2622   0.01713   0.00900  -0.1334   0.1977   1.0000
   6.750   1.3026   0.01872   0.01035  -0.1313   0.1420   1.0000
   7.000   1.3216   0.01960   0.01109  -0.1301   0.1138   1.0000
   7.250   1.3403   0.02048   0.01188  -0.1289   0.0941   1.0000
   7.500   1.3590   0.02133   0.01270  -0.1276   0.0819   1.0000
   7.750   1.3772   0.02219   0.01358  -0.1263   0.0730   1.0000
   8.000   1.3949   0.02305   0.01447  -0.1248   0.0660   1.0000
   8.250   1.4116   0.02395   0.01543  -0.1233   0.0612   1.0000
   8.500   1.4283   0.02480   0.01636  -0.1217   0.0573   1.0000
   8.750   1.4420   0.02574   0.01735  -0.1196   0.0540   1.0000
   9.000   1.4525   0.02684   0.01849  -0.1172   0.0514   1.0000
   9.250   1.4653   0.02779   0.01958  -0.1151   0.0495   1.0000
   9.500   1.4769   0.02883   0.02074  -0.1129   0.0477   1.0000
   9.750   1.4881   0.02992   0.02192  -0.1109   0.0457   1.0000
  10.000   1.4978   0.03115   0.02320  -0.1088   0.0435   1.0000
  10.250   1.5034   0.03276   0.02484  -0.1064   0.0415   1.0000
  10.500   1.5146   0.03397   0.02621  -0.1047   0.0399   1.0000
  10.750   1.5244   0.03534   0.02771  -0.1031   0.0381   1.0000
  11.000   1.5330   0.03683   0.02931  -0.1014   0.0363   1.0000
  11.250   1.5394   0.03858   0.03117  -0.0998   0.0347   1.0000
  11.500   1.5413   0.04088   0.03352  -0.0981   0.0331   1.0000
  11.750   1.5494   0.04263   0.03544  -0.0968   0.0318   1.0000
  12.000   1.5561   0.04456   0.03754  -0.0956   0.0303   1.0000
  12.250   1.5617   0.04664   0.03975  -0.0945   0.0287   1.0000
  12.500   1.5654   0.04897   0.04220  -0.0936   0.0273   1.0000
  12.750   1.5647   0.05190   0.04520  -0.0927   0.0261   1.0000
  13.000   1.5679   0.05452   0.04801  -0.0920   0.0249   1.0000
  13.250   1.5713   0.05719   0.05089  -0.0915   0.0234   1.0000
  13.500   1.5728   0.06014   0.05400  -0.0912   0.0220   1.0000
  13.750   1.5734   0.06326   0.05726  -0.0911   0.0209   1.0000
  14.000   1.5715   0.06680   0.06092  -0.0914   0.0200   1.0000
  14.250   1.5687   0.07066   0.06497  -0.0917   0.0191   1.0000
  14.500   1.5672   0.07448   0.06901  -0.0922   0.0180   1.0000
  14.750   1.5634   0.07875   0.07346  -0.0930   0.0172   1.0000
  15.000   1.5592   0.08323   0.07810  -0.0941   0.0165   1.0000
  15.250   1.5543   0.08800   0.08303  -0.0956   0.0159   1.0000
  15.500   1.5481   0.09310   0.08828  -0.0974   0.0154   1.0000
  15.750   1.5402   0.09868   0.09400  -0.0997   0.0150   1.0000
  16.000   1.5304   0.10479   0.10023  -0.1023   0.0147   1.0000
  16.250   1.5213   0.11093   0.10658  -0.1050   0.0143   1.0000
  16.500   1.5112   0.11745   0.11331  -0.1081   0.0140   1.0000
  16.750   1.5004   0.12427   0.12034  -0.1117   0.0136   1.0000
  17.000   1.4896   0.13131   0.12756  -0.1156   0.0133   1.0000
  17.250   1.4777   0.13877   0.13521  -0.1200   0.0131   1.0000
  17.500   1.4650   0.14665   0.14327  -0.1249   0.0129   1.0000
  17.750   1.4520   0.15487   0.15167  -0.1303   0.0127   1.0000
  18.000   1.4369   0.16390   0.16088  -0.1363   0.0126   1.0000
  18.250   1.4199   0.17393   0.17109  -0.1433   0.0125   1.0000
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