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GOE 364 AIRFOIL (goe364-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 364 AIRFOIL (goe364-il)
Reynolds number: 500,000
Max Cl/Cd: 107.79 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe364-il-500000.txt
Download as CSV file: xf-goe364-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 364 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.2293   0.11924   0.11700  -0.0327   1.0000   0.0184
 -10.500  -0.2280   0.11687   0.11465  -0.0324   1.0000   0.0189
 -10.250  -0.2276   0.11458   0.11240  -0.0319   1.0000   0.0193
 -10.000  -0.2224   0.11152   0.10935  -0.0338   0.9993   0.0198
  -9.750  -0.2072   0.10721   0.10504  -0.0406   0.9965   0.0200
  -9.500  -0.1948   0.10287   0.10071  -0.0477   0.9922   0.0200
  -9.250  -0.1742   0.09829   0.09612  -0.0495   0.9889   0.0202
  -9.000  -0.1521   0.09462   0.09245  -0.0522   0.9854   0.0204
  -8.750  -0.1330   0.09109   0.08893  -0.0559   0.9796   0.0207
  -8.500  -0.1137   0.08761   0.08544  -0.0600   0.9730   0.0212
  -8.250  -0.0947   0.08406   0.08188  -0.0644   0.9641   0.0219
  -8.000  -0.0675   0.07930   0.07710  -0.0736   0.9563   0.0234
  -7.750  -0.0458   0.07375   0.07150  -0.0871   0.9314   0.0236
  -7.500   0.0337   0.05560   0.05300  -0.0847   0.8238   0.0244
  -7.250   0.0364   0.05330   0.05062  -0.0846   0.8067   0.0247
  -7.000   0.0135   0.06373   0.06112  -0.0957   0.8461   0.0245
  -6.750   0.0229   0.06143   0.05869  -0.0969   0.8217   0.0249
  -6.500   0.0327   0.05903   0.05617  -0.0983   0.8042   0.0255
  -6.250   0.0441   0.05640   0.05344  -0.1002   0.7901   0.0263
  -5.750   0.0745   0.04746   0.04418  -0.1087   0.7673   0.0281
  -5.500   0.0895   0.04562   0.04229  -0.1084   0.7581   0.0284
  -5.250   0.1064   0.04375   0.04033  -0.1085   0.7491   0.0289
  -5.000   0.1252   0.04160   0.03810  -0.1092   0.7405   0.0297
  -4.750   0.1559   0.03664   0.03263  -0.1121   0.7327   0.0327
  -4.500   0.1704   0.03378   0.02976  -0.1120   0.7250   0.0332
  -4.250   0.1899   0.03240   0.02833  -0.1117   0.7170   0.0337
  -4.000   0.2111   0.03090   0.02673  -0.1115   0.7098   0.0344
  -3.750   0.2337   0.02912   0.02481  -0.1113   0.7022   0.0359
  -3.500   0.2578   0.02542   0.02060  -0.1107   0.6961   0.0392
  -3.250   0.2801   0.02430   0.01947  -0.1104   0.6883   0.0400
  -3.000   0.3033   0.02336   0.01841  -0.1099   0.6811   0.0414
  -2.750   0.3279   0.02121   0.01582  -0.1088   0.6739   0.0464
  -2.500   0.3511   0.02018   0.01475  -0.1083   0.6660   0.0474
  -2.250   0.3755   0.01939   0.01389  -0.1078   0.6580   0.0493
  -2.000   0.4004   0.01825   0.01237  -0.1068   0.6499   0.0553
  -1.750   0.4247   0.01741   0.01152  -0.1063   0.6407   0.0570
  -1.250   0.4744   0.01611   0.00996  -0.1050   0.6208   0.0676
  -1.000   0.5000   0.01585   0.00958  -0.1043   0.6109   0.0730
  -0.750   0.5242   0.01505   0.00866  -0.1037   0.5998   0.0804
  -0.500   0.5534   0.01267   0.00558  -0.1015   0.5897   0.0460
  -0.250   0.5792   0.01239   0.00520  -0.1008   0.5781   0.0457
   0.000   0.6042   0.01191   0.00463  -0.1000   0.5656   0.0452
   0.250   0.6291   0.01143   0.00410  -0.0992   0.5522   0.0448
   0.500   0.6540   0.01115   0.00376  -0.0984   0.5388   0.0447
   0.750   0.6788   0.01097   0.00352  -0.0976   0.5264   0.0450
   1.000   0.7034   0.01087   0.00335  -0.0968   0.5151   0.0453
   1.250   0.7277   0.01076   0.00319  -0.0960   0.5039   0.0457
   1.500   0.7521   0.01060   0.00301  -0.0952   0.4935   0.0475
   1.750   0.7766   0.01060   0.00296  -0.0944   0.4843   0.0493
   2.000   0.8019   0.01061   0.00293  -0.0938   0.4758   0.0509
   2.250   0.8268   0.01067   0.00294  -0.0931   0.4684   0.0532
   2.500   0.8522   0.01070   0.00296  -0.0925   0.4612   0.0582
   2.750   0.9216   0.00912   0.00336  -0.1023   0.4522   1.0000
   3.000   0.9462   0.00926   0.00344  -0.1016   0.4456   1.0000
   3.250   0.9696   0.00947   0.00355  -0.1006   0.4389   1.0000
   3.500   0.9942   0.00960   0.00365  -0.0999   0.4326   1.0000
   3.750   1.0180   0.00977   0.00378  -0.0991   0.4261   1.0000
   4.000   1.0416   0.00997   0.00392  -0.0982   0.4203   1.0000
   4.250   1.0660   0.01010   0.00404  -0.0975   0.4141   1.0000
   4.500   1.0891   0.01031   0.00420  -0.0966   0.4077   1.0000
   4.750   1.1130   0.01046   0.00435  -0.0958   0.4011   1.0000
   5.000   1.1363   0.01064   0.00449  -0.0949   0.3938   1.0000
   5.250   1.1593   0.01083   0.00466  -0.0940   0.3867   1.0000
   5.500   1.1825   0.01099   0.00483  -0.0931   0.3788   1.0000
   5.750   1.2049   0.01120   0.00500  -0.0921   0.3706   1.0000
   6.000   1.2272   0.01139   0.00517  -0.0911   0.3606   1.0000
   6.250   1.2493   0.01159   0.00537  -0.0900   0.3494   1.0000
   6.500   1.2700   0.01184   0.00557  -0.0888   0.3354   1.0000
   6.750   1.2896   0.01214   0.00580  -0.0873   0.3187   1.0000
   7.000   1.3084   0.01249   0.00607  -0.0858   0.3031   1.0000
   7.250   1.3266   0.01286   0.00638  -0.0842   0.2897   1.0000
   7.500   1.3440   0.01326   0.00672  -0.0824   0.2783   1.0000
   7.750   1.3606   0.01368   0.00709  -0.0805   0.2684   1.0000
   8.000   1.3772   0.01403   0.00744  -0.0786   0.2608   1.0000
   8.250   1.3917   0.01445   0.00783  -0.0763   0.2542   1.0000
   8.500   1.4075   0.01484   0.00822  -0.0743   0.2489   1.0000
   8.750   1.4239   0.01521   0.00862  -0.0725   0.2438   1.0000
   9.000   1.4378   0.01571   0.00909  -0.0703   0.2386   1.0000
   9.250   1.4539   0.01612   0.00954  -0.0685   0.2337   1.0000
   9.500   1.4702   0.01654   0.00999  -0.0668   0.2288   1.0000
   9.750   1.4828   0.01713   0.01056  -0.0647   0.2231   1.0000
  10.000   1.4990   0.01757   0.01106  -0.0631   0.2185   1.0000
  10.250   1.5145   0.01805   0.01158  -0.0615   0.2131   1.0000
  10.500   1.5265   0.01872   0.01224  -0.0595   0.2083   1.0000
  10.750   1.5417   0.01925   0.01283  -0.0580   0.2040   1.0000
  11.000   1.5570   0.01979   0.01343  -0.0566   0.1989   1.0000
  11.250   1.5678   0.02059   0.01423  -0.0547   0.1933   1.0000
  11.500   1.5828   0.02118   0.01489  -0.0534   0.1877   1.0000
  11.750   1.5955   0.02194   0.01568  -0.0519   0.1817   1.0000
  12.000   1.6059   0.02287   0.01663  -0.0503   0.1763   1.0000
  12.250   1.6195   0.02363   0.01747  -0.0491   0.1700   1.0000
  12.500   1.6273   0.02483   0.01865  -0.0475   0.1634   1.0000
  12.750   1.6391   0.02580   0.01968  -0.0464   0.1557   1.0000
  13.000   1.6458   0.02718   0.02107  -0.0450   0.1483   1.0000
  13.250   1.6524   0.02863   0.02254  -0.0437   0.1401   1.0000
  13.500   1.6569   0.03030   0.02422  -0.0425   0.1318   1.0000
  13.750   1.6583   0.03231   0.02623  -0.0412   0.1239   1.0000
  14.000   1.6614   0.03422   0.02817  -0.0401   0.1168   1.0000
  14.250   1.6612   0.03649   0.03046  -0.0391   0.1100   1.0000
  14.500   1.6596   0.03898   0.03297  -0.0381   0.1027   1.0000
  14.750   1.6588   0.04146   0.03550  -0.0374   0.0966   1.0000
  15.000   1.6532   0.04450   0.03854  -0.0366   0.0897   1.0000
  15.250   1.6469   0.04772   0.04177  -0.0361   0.0808   1.0000
  15.500   1.6410   0.05100   0.04508  -0.0357   0.0735   1.0000
  15.750   1.6292   0.05506   0.04914  -0.0355   0.0635   1.0000
  16.000   1.6111   0.06004   0.05409  -0.0356   0.0512   1.0000
  16.250   1.5889   0.06571   0.05972  -0.0361   0.0382   1.0000
  16.500   1.5626   0.07220   0.06621  -0.0369   0.0274   1.0000
  16.750   1.5439   0.07790   0.07197  -0.0379   0.0236   1.0000
  17.000   1.5271   0.08347   0.07762  -0.0391   0.0212   1.0000
  17.250   1.5157   0.08841   0.08267  -0.0402   0.0203   1.0000
  17.500   1.5025   0.09369   0.08806  -0.0415   0.0195   1.0000
  17.750   1.4891   0.09907   0.09356  -0.0430   0.0189   1.0000
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