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FX 67-K-170/17 AIRFOIL (fx67k170-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX 67-K-170/17 AIRFOIL (fx67k170-il)
Reynolds number: 200,000
Max Cl/Cd: 36.58 at α=11.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx67k170-il-200000.txt
Download as CSV file: xf-fx67k170-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 67-K-170/17 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.0679   0.11165   0.10749  -0.1070   0.8077   0.0385
 -11.500  -0.0664   0.10848   0.10434  -0.1089   0.8056   0.0402
 -11.250  -0.0723   0.10509   0.10099  -0.1124   0.8035   0.0417
 -11.000  -0.0790   0.10159   0.09753  -0.1160   0.8017   0.0422
 -10.750  -0.0811   0.09799   0.09394  -0.1185   0.8001   0.0423
 -10.500  -0.0771   0.09308   0.08904  -0.1178   0.7989   0.0435
 -10.250  -0.0651   0.09099   0.08697  -0.1172   0.7970   0.0445
 -10.000  -0.0571   0.08864   0.08465  -0.1177   0.7945   0.0459
  -9.750  -0.0542   0.08581   0.08185  -0.1189   0.7920   0.0476
  -9.500  -0.0550   0.08253   0.07859  -0.1206   0.7896   0.0492
  -9.250  -0.0599   0.07866   0.07476  -0.1230   0.7876   0.0507
  -9.000  -0.0704   0.07385   0.06997  -0.1270   0.7857   0.0517
  -8.750  -0.0950   0.06879   0.06487  -0.1315   0.7832   0.0525
  -8.500  -0.1149   0.06627   0.06236  -0.1318   0.7790   0.0527
  -8.250  -0.1454   0.06511   0.06098  -0.1296   0.7751   0.0537
  -8.000  -0.1638   0.06467   0.06020  -0.1267   0.7725   0.0543
  -7.750  -0.1682   0.05836   0.05388  -0.1263   0.7710   0.0556
  -7.500  -0.1521   0.05573   0.05135  -0.1260   0.7699   0.0576
  -7.250  -0.1492   0.05460   0.05025  -0.1252   0.7650   0.0594
  -7.000  -0.1476   0.05338   0.04884  -0.1234   0.7615   0.0648
  -6.750  -0.1546   0.05086   0.04588  -0.1207   0.7587   0.0694
  -6.500  -0.1367   0.04867   0.04380  -0.1203   0.7573   0.0732
  -5.500  -0.1083   0.03799   0.03129  -0.1089   0.7442   0.0447
  -5.250  -0.0834   0.03545   0.02842  -0.1077   0.7429   0.0389
  -5.000  -0.0580   0.03320   0.02580  -0.1067   0.7419   0.0374
  -4.750  -0.0308   0.03171   0.02404  -0.1062   0.7411   0.0382
  -3.750  -0.0353   0.03433   0.02633  -0.0916   0.7196   0.0424
  -3.500  -0.0179   0.03297   0.02499  -0.0901   0.7173   0.0448
  -3.250   0.0094   0.03240   0.02442  -0.0901   0.7158   0.0502
  -3.000   0.0407   0.03173   0.02368  -0.0905   0.7147   0.0553
  -2.750   0.0041   0.03391   0.02584  -0.0820   0.7070   0.0543
  -2.500   0.0168   0.03368   0.02565  -0.0803   0.7039   0.0591
  -2.250   0.0423   0.03339   0.02531  -0.0800   0.7021   0.0644
  -2.000   0.0731   0.03288   0.02477  -0.0805   0.7008   0.0749
  -1.750   0.0996   0.03152   0.02423  -0.0808   0.6999   0.2589
  -1.500   0.0727   0.03348   0.02639  -0.0746   0.6927   0.3074
  -1.250   0.0698   0.03250   0.02720  -0.0687   0.6895   0.7346
  -1.000   0.0876   0.03292   0.02760  -0.0660   0.6877   0.8027
  -0.750   0.1074   0.03321   0.02785  -0.0635   0.6864   0.8390
  -0.500   0.1185   0.03333   0.02801  -0.0584   0.6853   0.8814
  -0.250   0.1283   0.03320   0.02790  -0.0527   0.6845   0.9191
   0.000   0.0934   0.03532   0.03011  -0.0463   0.6745   0.9322
   0.250   0.1399   0.03574   0.03045  -0.0494   0.6733   0.9629
   0.500   0.2093   0.03639   0.03094  -0.0573   0.6725   0.9772
   0.750   0.2748   0.03685   0.03125  -0.0645   0.6718   0.9843
   1.000   0.3240   0.03698   0.03126  -0.0686   0.6711   0.9874
   1.250   0.3721   0.03702   0.03121  -0.0724   0.6705   0.9908
   1.500   0.3388   0.03954   0.03377  -0.0676   0.6597   1.0000
   1.750   0.3589   0.03931   0.03346  -0.0664   0.6582   1.0000
   2.000   0.3247   0.04069   0.03484  -0.0592   0.6495   1.0000
   2.250   0.3461   0.04099   0.03507  -0.0589   0.6468   1.0000
   2.500   0.3763   0.04106   0.03507  -0.0595   0.6450   1.0000
   2.750   0.4102   0.04103   0.03497  -0.0606   0.6438   1.0000
   3.000   0.4451   0.04101   0.03490  -0.0617   0.6430   1.0000
   3.250   0.4292   0.04309   0.03697  -0.0584   0.6323   1.0000
   3.500   0.4621   0.04311   0.03695  -0.0593   0.6307   1.0000
   3.750   0.4977   0.04301   0.03680  -0.0605   0.6296   1.0000
   4.000   0.5336   0.04292   0.03668  -0.0617   0.6288   1.0000
   4.250   0.5192   0.04516   0.03893  -0.0586   0.6176   1.0000
   4.500   0.5538   0.04503   0.03877  -0.0597   0.6163   1.0000
   4.750   0.5765   0.04555   0.03929  -0.0597   0.6127   1.0000
   5.000   0.6256   0.04465   0.03838  -0.0619   0.6145   1.0000
   5.250   0.6137   0.04683   0.04057  -0.0590   0.6028   1.0000
   5.500   0.6488   0.04656   0.04030  -0.0600   0.6017   1.0000
   5.750   0.6845   0.04628   0.04003  -0.0610   0.6008   1.0000
   6.000   0.6760   0.04840   0.04218  -0.0584   0.5893   1.0000
   6.250   0.7102   0.04810   0.04190  -0.0593   0.5880   1.0000
   6.500   0.7461   0.04766   0.04147  -0.0602   0.5871   1.0000
   6.750   0.7838   0.04699   0.04085  -0.0612   0.5862   1.0000
   7.000   0.7775   0.04900   0.04289  -0.0588   0.5743   1.0000
   7.250   0.7815   0.05049   0.04442  -0.0573   0.5649   1.0000
   7.500   0.8226   0.04898   0.04294  -0.0581   0.5623   1.0000
   7.750   0.8668   0.04717   0.04121  -0.0591   0.5609   1.0000
   8.000   0.9073   0.04582   0.03991  -0.0601   0.5599   1.0000
   8.250   0.9462   0.04460   0.03879  -0.0609   0.5591   1.0000
   8.500   0.9845   0.04342   0.03768  -0.0617   0.5584   1.0000
   8.750   1.0261   0.04179   0.03615  -0.0627   0.5580   1.0000
   9.250   1.0465   0.04339   0.03791  -0.0600   0.5410   1.0000
   9.500   1.0961   0.04072   0.03536  -0.0613   0.5419   1.0000
   9.750   1.1520   0.03745   0.03223  -0.0631   0.5427   1.0000
  10.000   1.1611   0.03806   0.03293  -0.0614   0.5321   1.0000
  10.250   1.2179   0.03480   0.02980  -0.0633   0.5303   1.0000
  10.500   1.2275   0.03529   0.03036  -0.0616   0.5170   1.0000
  10.750   1.2441   0.03531   0.03045  -0.0605   0.5026   1.0000
  11.000   1.2617   0.03551   0.03074  -0.0596   0.4883   1.0000
  11.250   1.2808   0.03562   0.03089  -0.0588   0.4707   1.0000
  11.500   1.3005   0.03555   0.03076  -0.0579   0.4424   1.0000
  11.750   1.3144   0.03596   0.03101  -0.0565   0.4064   1.0000
  12.000   1.3131   0.03759   0.03231  -0.0540   0.3611   1.0000
  12.250   1.3034   0.04020   0.03466  -0.0513   0.3213   1.0000
  12.500   1.2893   0.04338   0.03759  -0.0487   0.2806   1.0000
  12.750   1.2725   0.04703   0.04096  -0.0462   0.2382   1.0000
  13.000   1.2555   0.05092   0.04458  -0.0440   0.1950   1.0000
  13.250   1.2383   0.05502   0.04835  -0.0421   0.1497   1.0000
  13.500   1.2232   0.05907   0.05209  -0.0406   0.1097   1.0000
  13.750   1.2159   0.06250   0.05533  -0.0395   0.0870   1.0000
  14.000   1.2140   0.06545   0.05821  -0.0388   0.0741   1.0000
  14.250   1.2141   0.06826   0.06099  -0.0383   0.0652   1.0000
  14.500   1.2158   0.07094   0.06369  -0.0379   0.0587   1.0000
  14.750   1.2184   0.07358   0.06640  -0.0376   0.0536   1.0000
  15.000   1.2212   0.07625   0.06913  -0.0374   0.0484   1.0000
  15.250   1.2213   0.07930   0.07224  -0.0371   0.0423   1.0000
  15.500   1.2142   0.08328   0.07623  -0.0369   0.0343   1.0000
  15.750   1.2047   0.08763   0.08059  -0.0367   0.0279   1.0000
  16.000   1.2041   0.09095   0.08402  -0.0365   0.0230   1.0000
  16.250   1.2042   0.09421   0.08733  -0.0367   0.0207   1.0000
  16.500   1.2065   0.09712   0.09032  -0.0367   0.0188   1.0000
  16.750   1.2112   0.09988   0.09318  -0.0371   0.0170   1.0000
  17.000   1.2148   0.10277   0.09612  -0.0377   0.0159   1.0000
  17.250   1.2161   0.10583   0.09920  -0.0380   0.0147   1.0000
  17.500   1.2221   0.10824   0.10174  -0.0381   0.0140   1.0000
  17.750   1.2291   0.11045   0.10406  -0.0381   0.0135   1.0000
  18.000   1.2358   0.11277   0.10649  -0.0383   0.0129   1.0000
  18.250   1.2432   0.11492   0.10875  -0.0384   0.0126   1.0000
  18.500   1.2485   0.11747   0.11141  -0.0388   0.0121   1.0000
  18.750   1.2537   0.12004   0.11409  -0.0393   0.0118   1.0000
  19.000   1.2586   0.12266   0.11685  -0.0398   0.0116   1.0000
  19.250   1.2626   0.12543   0.11977  -0.0403   0.0114   1.0000
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