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FX 63-110 AIRFOIL (fx63110-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: FX 63-110 AIRFOIL (fx63110-il)
Reynolds number: 500,000
Max Cl/Cd: 118.34 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx63110-il-500000.txt
Download as CSV file: xf-fx63110-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 63-110 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3535   0.09220   0.08995  -0.0397   1.0000   0.0285
  -9.000  -0.3562   0.08958   0.08737  -0.0394   1.0000   0.0290
  -8.750  -0.4546   0.02522   0.02117  -0.1158   0.9759   0.0222
  -8.500  -0.4187   0.02394   0.01982  -0.1190   0.9738   0.0230
  -8.250  -0.3836   0.02279   0.01856  -0.1217   0.9710   0.0238
  -8.000  -0.3516   0.02103   0.01651  -0.1239   0.9652   0.0251
  -7.750  -0.3140   0.01975   0.01487  -0.1268   0.9623   0.0264
  -7.500  -0.2781   0.01786   0.01290  -0.1298   0.9602   0.0280
  -7.250  -0.2469   0.01720   0.01218  -0.1308   0.9538   0.0293
  -7.000  -0.2114   0.01623   0.01104  -0.1327   0.9497   0.0308
  -6.750  -0.1729   0.01522   0.00982  -0.1352   0.9468   0.0323
  -6.500  -0.1393   0.01413   0.00873  -0.1369   0.9404   0.0342
  -6.250  -0.1021   0.01354   0.00809  -0.1390   0.9352   0.0360
  -6.000  -0.0637   0.01290   0.00734  -0.1413   0.9301   0.0377
  -5.750  -0.0280   0.01205   0.00639  -0.1431   0.9222   0.0396
  -5.500   0.0088   0.01139   0.00571  -0.1452   0.9150   0.0417
  -5.250   0.0424   0.01098   0.00524  -0.1464   0.9053   0.0437
  -5.000   0.0745   0.01069   0.00486  -0.1473   0.8956   0.0458
  -4.750   0.1066   0.01020   0.00427  -0.1482   0.8863   0.0478
  -4.500   0.1362   0.00982   0.00386  -0.1487   0.8755   0.0506
  -4.250   0.1658   0.00963   0.00360  -0.1489   0.8646   0.0538
  -4.000   0.1954   0.00940   0.00327  -0.1492   0.8537   0.0573
  -3.750   0.2244   0.00913   0.00299  -0.1494   0.8428   0.0635
  -3.500   0.2541   0.00890   0.00275  -0.1498   0.8343   0.0742
  -3.250   0.2833   0.00871   0.00257  -0.1500   0.8254   0.0946
  -3.000   0.3130   0.00847   0.00238  -0.1504   0.8172   0.1207
  -2.750   0.3431   0.00812   0.00220  -0.1511   0.8087   0.1769
  -2.500   0.3741   0.00763   0.00213  -0.1522   0.8008   0.3314
  -2.250   0.4031   0.00753   0.00210  -0.1524   0.7925   0.3759
  -2.000   0.4321   0.00747   0.00207  -0.1525   0.7846   0.4052
  -1.750   0.4609   0.00741   0.00204  -0.1526   0.7763   0.4329
  -1.500   0.4900   0.00733   0.00206  -0.1528   0.7686   0.4755
  -1.250   0.5187   0.00729   0.00213  -0.1529   0.7605   0.5243
  -1.000   0.5472   0.00733   0.00218  -0.1528   0.7525   0.5539
  -0.750   0.5756   0.00737   0.00221  -0.1527   0.7443   0.5758
  -0.500   0.6039   0.00742   0.00226  -0.1526   0.7365   0.5952
  -0.250   0.6321   0.00747   0.00230  -0.1525   0.7281   0.6107
   0.000   0.6603   0.00753   0.00235  -0.1524   0.7199   0.6252
   0.250   0.6883   0.00759   0.00239  -0.1522   0.7115   0.6390
   0.500   0.7162   0.00764   0.00246  -0.1521   0.7029   0.6526
   0.750   0.7439   0.00771   0.00252  -0.1518   0.6941   0.6649
   1.000   0.7716   0.00776   0.00256  -0.1516   0.6826   0.6748
   1.250   0.7989   0.00783   0.00261  -0.1513   0.6695   0.6838
   1.500   0.8261   0.00790   0.00266  -0.1510   0.6566   0.6921
   1.750   0.8534   0.00801   0.00273  -0.1507   0.6452   0.7010
   2.000   0.8809   0.00807   0.00281  -0.1505   0.6337   0.7094
   2.250   0.9083   0.00817   0.00290  -0.1503   0.6219   0.7188
   2.500   0.9353   0.00826   0.00300  -0.1500   0.6096   0.7270
   2.750   0.9622   0.00839   0.00310  -0.1496   0.5941   0.7361
   3.000   0.9886   0.00850   0.00321  -0.1492   0.5765   0.7447
   3.250   1.0151   0.00864   0.00333  -0.1488   0.5593   0.7544
   3.500   1.0414   0.00880   0.00347  -0.1485   0.5418   0.7653
   4.000   1.0918   0.00923   0.00380  -0.1473   0.4930   0.7881
   4.250   1.1162   0.00950   0.00400  -0.1466   0.4664   0.8027
   4.500   1.1403   0.00977   0.00423  -0.1458   0.4434   0.8208
   4.750   1.1641   0.01001   0.00447  -0.1449   0.4236   0.8437
   5.000   1.1853   0.01019   0.00470  -0.1435   0.4023   0.8798
   5.250   1.2028   0.01031   0.00484  -0.1412   0.3814   1.0000
   5.500   1.2281   0.01071   0.00512  -0.1409   0.3531   1.0000
   5.750   1.2523   0.01119   0.00546  -0.1404   0.3205   1.0000
   6.000   1.2752   0.01177   0.00584  -0.1397   0.2837   1.0000
   6.250   1.2973   0.01243   0.00630  -0.1388   0.2460   1.0000
   6.500   1.3191   0.01310   0.00680  -0.1380   0.2148   1.0000
   6.750   1.3411   0.01373   0.00730  -0.1371   0.1884   1.0000
   7.000   1.3625   0.01441   0.00783  -0.1362   0.1610   1.0000
   7.250   1.3826   0.01519   0.00842  -0.1351   0.1289   1.0000
   7.500   1.4012   0.01609   0.00912  -0.1338   0.0987   1.0000
   7.750   1.4203   0.01690   0.00983  -0.1325   0.0813   1.0000
   8.000   1.4392   0.01770   0.01056  -0.1312   0.0689   1.0000
   8.250   1.4572   0.01854   0.01135  -0.1297   0.0600   1.0000
   8.500   1.4770   0.01916   0.01200  -0.1285   0.0549   1.0000
   8.750   1.4931   0.02004   0.01287  -0.1267   0.0504   1.0000
   9.000   1.5123   0.02062   0.01351  -0.1254   0.0480   1.0000
   9.250   1.5288   0.02130   0.01421  -0.1237   0.0455   1.0000
   9.500   1.5401   0.02220   0.01513  -0.1211   0.0431   1.0000
   9.750   1.5504   0.02314   0.01614  -0.1185   0.0414   1.0000
  10.000   1.5640   0.02388   0.01695  -0.1164   0.0400   1.0000
  10.250   1.5763   0.02473   0.01787  -0.1143   0.0386   1.0000
  10.500   1.5868   0.02572   0.01890  -0.1120   0.0371   1.0000
  10.750   1.5926   0.02708   0.02031  -0.1094   0.0356   1.0000
  11.000   1.5949   0.02880   0.02211  -0.1065   0.0343   1.0000
  11.250   1.6066   0.02985   0.02327  -0.1049   0.0334   1.0000
  11.500   1.6158   0.03115   0.02465  -0.1031   0.0323   1.0000
  11.750   1.6239   0.03258   0.02616  -0.1014   0.0311   1.0000
  12.000   1.6305   0.03421   0.02785  -0.0998   0.0300   1.0000
  12.250   1.6304   0.03656   0.03025  -0.0979   0.0289   1.0000
  12.500   1.6304   0.03904   0.03285  -0.0961   0.0279   1.0000
  12.750   1.6397   0.04066   0.03458  -0.0952   0.0270   1.0000
  13.000   1.6464   0.04258   0.03661  -0.0942   0.0260   1.0000
  13.250   1.6514   0.04474   0.03885  -0.0933   0.0251   1.0000
  13.500   1.6551   0.04711   0.04129  -0.0925   0.0243   1.0000
  13.750   1.6540   0.05014   0.04439  -0.0918   0.0235   1.0000
  14.000   1.6475   0.05395   0.04830  -0.0910   0.0227   1.0000
  14.250   1.6530   0.05638   0.05086  -0.0908   0.0221   1.0000
  14.500   1.6565   0.05913   0.05376  -0.0907   0.0213   1.0000
  14.750   1.6587   0.06213   0.05686  -0.0907   0.0206   1.0000
  15.000   1.6599   0.06534   0.06016  -0.0910   0.0200   1.0000
  15.250   1.6596   0.06887   0.06377  -0.0914   0.0194   1.0000
  15.500   1.6552   0.07310   0.06807  -0.0921   0.0189   1.0000
  15.750   1.6463   0.07809   0.07317  -0.0928   0.0184   1.0000
  16.000   1.6457   0.08206   0.07730  -0.0939   0.0180   1.0000
  16.250   1.6431   0.08645   0.08184  -0.0951   0.0176   1.0000
  16.500   1.6401   0.09101   0.08654  -0.0965   0.0171   1.0000
  16.750   1.6357   0.09587   0.09153  -0.0982   0.0168   1.0000
  17.000   1.6315   0.10080   0.09659  -0.1001   0.0164   1.0000
  17.250   1.6270   0.10587   0.10177  -0.1022   0.0160   1.0000
  17.500   1.6224   0.11105   0.10705  -0.1045   0.0157   1.0000
  17.750   1.6170   0.11639   0.11248  -0.1069   0.0154   1.0000
  18.000   1.6097   0.12207   0.11824  -0.1096   0.0151   1.0000
  18.250   1.5997   0.12810   0.12437  -0.1124   0.0147   1.0000
  18.500   1.5933   0.13397   0.13041  -0.1156   0.0146   1.0000
  18.750   1.5864   0.13998   0.13658  -0.1191   0.0144   1.0000
  19.000   1.5788   0.14630   0.14305  -0.1229   0.0141   1.0000
  19.250   1.5705   0.15270   0.14960  -0.1269   0.0138   1.0000
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