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FX 67-K-170/17 AIRFOIL (fx67k170-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: FX 67-K-170/17 AIRFOIL (fx67k170-il)
Reynolds number: 200,000
Max Cl/Cd: 48.24 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx67k170-il-200000-n5.txt
Download as CSV file: xf-fx67k170-il-200000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.1032   0.09548   0.09074  -0.1043   0.7540   0.0138
 -11.000  -0.1028   0.09149   0.08679  -0.1060   0.7522   0.0137
 -10.750  -0.1018   0.08783   0.08317  -0.1076   0.7505   0.0136
 -10.500  -0.1021   0.08402   0.07939  -0.1094   0.7488   0.0134
 -10.250  -0.1029   0.08020   0.07560  -0.1112   0.7471   0.0133
 -10.000  -0.1076   0.07549   0.07092  -0.1136   0.7454   0.0131
  -9.750  -0.1166   0.06974   0.06520  -0.1170   0.7438   0.0130
  -9.500  -0.1307   0.06276   0.05819  -0.1223   0.7422   0.0127
  -9.250  -0.1506   0.05738   0.05275  -0.1251   0.7404   0.0125
  -9.000  -0.1707   0.05339   0.04871  -0.1254   0.7376   0.0123
  -8.750  -0.1931   0.05025   0.04545  -0.1232   0.7349   0.0124
  -8.500  -0.2064   0.04701   0.04202  -0.1211   0.7327   0.0123
  -8.250  -0.2154   0.04341   0.03814  -0.1189   0.7308   0.0124
  -8.000  -0.2207   0.03948   0.03378  -0.1163   0.7291   0.0132
  -7.750  -0.2197   0.03593   0.02969  -0.1139   0.7276   0.0136
  -7.500  -0.2126   0.03316   0.02645  -0.1119   0.7258   0.0141
  -7.250  -0.1993   0.03125   0.02431  -0.1107   0.7232   0.0143
  -7.000  -0.1826   0.02962   0.02245  -0.1097   0.7210   0.0145
  -6.750  -0.1636   0.02821   0.02082  -0.1089   0.7191   0.0149
  -6.500  -0.1429   0.02682   0.01920  -0.1082   0.7174   0.0154
  -6.250  -0.1207   0.02547   0.01759  -0.1076   0.7159   0.0161
  -6.000  -0.0972   0.02417   0.01603  -0.1070   0.7145   0.0169
  -5.750  -0.0725   0.02305   0.01464  -0.1065   0.7133   0.0179
  -5.500  -0.0493   0.02214   0.01363  -0.1061   0.7115   0.0194
  -5.250  -0.0272   0.02167   0.01318  -0.1057   0.7089   0.0212
  -5.000  -0.0042   0.02104   0.01249  -0.1052   0.7067   0.0227
  -4.750   0.0191   0.02042   0.01178  -0.1046   0.7048   0.0243
  -4.500   0.0411   0.01967   0.01100  -0.1040   0.7031   0.0265
  -4.250   0.0654   0.01925   0.01055  -0.1037   0.7016   0.0297
  -4.000   0.0904   0.01886   0.01006  -0.1034   0.7003   0.0326
  -3.750   0.1143   0.01827   0.00942  -0.1031   0.6991   0.0358
  -3.500   0.1374   0.01806   0.00916  -0.1026   0.6970   0.0387
  -3.250   0.1595   0.01802   0.00908  -0.1020   0.6942   0.0423
  -3.000   0.1826   0.01779   0.00885  -0.1016   0.6919   0.0482
  -2.750   0.2068   0.01753   0.00861  -0.1013   0.6901   0.0632
  -2.500   0.2289   0.01686   0.00831  -0.1009   0.6884   0.1638
  -2.250   0.2485   0.01587   0.00804  -0.1003   0.6870   0.3600
  -2.000   0.2649   0.01490   0.00800  -0.0985   0.6857   0.5979
  -1.750   0.2841   0.01493   0.00847  -0.0958   0.6847   0.7376
  -1.500   0.3010   0.01549   0.00907  -0.0939   0.6812   0.7759
  -1.250   0.3217   0.01584   0.00938  -0.0927   0.6785   0.7940
  -1.000   0.3439   0.01606   0.00957  -0.0915   0.6764   0.8105
  -0.750   0.3671   0.01619   0.00964  -0.0904   0.6747   0.8252
  -0.500   0.3922   0.01624   0.00961  -0.0899   0.6733   0.8361
  -0.250   0.4187   0.01623   0.00952  -0.0896   0.6721   0.8424
   0.000   0.4461   0.01622   0.00943  -0.0896   0.6711   0.8491
   0.250   0.4641   0.01659   0.00980  -0.0884   0.6681   0.8553
   0.500   0.4795   0.01701   0.01024  -0.0867   0.6643   0.8614
   0.750   0.5030   0.01714   0.01032  -0.0863   0.6621   0.8676
   1.000   0.5278   0.01715   0.01030  -0.0859   0.6604   0.8721
   1.250   0.5544   0.01714   0.01025  -0.0859   0.6591   0.8771
   1.750   0.6104   0.01709   0.01011  -0.0864   0.6571   0.8855
   2.250   0.6288   0.01828   0.01140  -0.0814   0.6482   0.8977
   2.500   0.6528   0.01834   0.01147  -0.0811   0.6465   0.9019
   2.750   0.6796   0.01835   0.01146  -0.0812   0.6452   0.9064
   3.000   0.7088   0.01829   0.01139  -0.0817   0.6442   0.9108
   3.250   0.7392   0.01818   0.01127  -0.0824   0.6433   0.9143
   3.750   0.7357   0.02004   0.01330  -0.0744   0.6320   0.9330
   4.000   0.7670   0.01995   0.01322  -0.0754   0.6310   0.9379
   4.250   0.8006   0.01983   0.01311  -0.0767   0.6301   0.9424
   4.500   0.8364   0.01970   0.01301  -0.0784   0.6294   0.9466
   4.750   0.8739   0.01953   0.01286  -0.0805   0.6287   0.9509
   5.250   0.8926   0.02192   0.01542  -0.0787   0.6162   1.0000
   5.500   0.9298   0.02139   0.01491  -0.0801   0.6154   1.0000
   5.750   0.9774   0.02026   0.01380  -0.0828   0.6143   1.0000
   6.000   0.9437   0.02317   0.01675  -0.0763   0.6022   1.0000
   6.250   0.9940   0.02157   0.01517  -0.0788   0.6010   1.0000
   6.750   1.0108   0.02333   0.01700  -0.0753   0.5876   1.0000
   7.000   1.0482   0.02267   0.01639  -0.0766   0.5864   1.0000
   7.500   1.0436   0.02595   0.01979  -0.0711   0.5694   1.0000
   8.000   1.0855   0.02638   0.02033  -0.0702   0.5591   1.0000
   8.250   1.0785   0.02847   0.02248  -0.0672   0.5479   1.0000
   8.500   1.1135   0.02771   0.02179  -0.0680   0.5448   1.0000
   9.000   1.1254   0.03021   0.02443  -0.0645   0.5247   1.0000
   9.250   1.1575   0.02944   0.02369  -0.0649   0.5150   1.0000
   9.500   1.1663   0.03047   0.02477  -0.0633   0.5018   1.0000
   9.750   1.1822   0.03095   0.02530  -0.0624   0.4874   1.0000
  10.000   1.1974   0.03145   0.02579  -0.0614   0.4670   1.0000
  10.250   1.2210   0.03123   0.02547  -0.0608   0.4403   1.0000
  10.500   1.2312   0.03185   0.02579  -0.0590   0.3977   1.0000
  10.750   1.2277   0.03372   0.02740  -0.0564   0.3594   1.0000
  11.000   1.2250   0.03575   0.02929  -0.0541   0.3300   1.0000
  11.250   1.2210   0.03801   0.03141  -0.0520   0.3005   1.0000
  11.500   1.2178   0.04034   0.03362  -0.0501   0.2728   1.0000
  11.750   1.2138   0.04282   0.03597  -0.0483   0.2445   1.0000
  12.000   1.2099   0.04541   0.03842  -0.0466   0.2162   1.0000
  12.250   1.2032   0.04833   0.04116  -0.0449   0.1839   1.0000
  12.500   1.1977   0.05123   0.04389  -0.0435   0.1519   1.0000
  12.750   1.1929   0.05416   0.04664  -0.0422   0.1204   1.0000
  13.250   1.1873   0.05987   0.05204  -0.0402   0.0702   1.0000
  13.500   1.1886   0.06242   0.05454  -0.0395   0.0578   1.0000
  13.750   1.1926   0.06476   0.05690  -0.0390   0.0501   1.0000
  14.000   1.1962   0.06717   0.05931  -0.0386   0.0439   1.0000
  14.250   1.2005   0.06956   0.06172  -0.0383   0.0387   1.0000
  14.500   1.2044   0.07202   0.06422  -0.0380   0.0346   1.0000
  14.750   1.2106   0.07426   0.06655  -0.0378   0.0312   1.0000
  15.000   1.2145   0.07683   0.06919  -0.0377   0.0287   1.0000
  15.250   1.2204   0.07918   0.07164  -0.0377   0.0257   1.0000
  15.500   1.2281   0.08133   0.07391  -0.0377   0.0200   1.0000
  15.750   1.2334   0.08380   0.07642  -0.0378   0.0147   1.0000
  16.000   1.2352   0.08673   0.07938  -0.0379   0.0117   1.0000
  16.250   1.2364   0.08981   0.08251  -0.0380   0.0102   1.0000
  16.500   1.2370   0.09302   0.08583  -0.0383   0.0091   1.0000
  16.750   1.2369   0.09637   0.08926  -0.0386   0.0083   1.0000
  17.000   1.2365   0.09979   0.09277  -0.0391   0.0077   1.0000
  17.250   1.2370   0.10314   0.09627  -0.0396   0.0070   1.0000
  17.500   1.2377   0.10648   0.09972  -0.0403   0.0065   1.0000
  17.750   1.2378   0.10996   0.10334  -0.0411   0.0062   1.0000
  18.000   1.2364   0.11370   0.10717  -0.0420   0.0058   1.0000
  18.250   1.2349   0.11751   0.11111  -0.0431   0.0057   1.0000
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