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Glenn Martin 3 (glennmartin3-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: Glenn Martin 3 (glennmartin3-il)
Reynolds number: 500,000
Max Cl/Cd: 62.83 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-glennmartin3-il-500000.txt
Download as CSV file: xf-glennmartin3-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Glenn Martin 3                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3403   0.07315   0.07083  -0.0852   0.9607   0.0314
  -9.250  -0.3521   0.06783   0.06545  -0.0868   0.9575   0.0317
  -9.000  -0.3451   0.06675   0.06436  -0.0857   0.9546   0.0319
  -7.750  -0.4424   0.03912   0.03524  -0.0644   0.9216   0.0319
  -7.500  -0.4263   0.03715   0.03323  -0.0629   0.9186   0.0322
  -7.250  -0.4292   0.03440   0.03032  -0.0573   0.9112   0.0296
  -7.000  -0.4282   0.02973   0.02504  -0.0523   0.9082   0.0297
  -6.750  -0.4129   0.02727   0.02216  -0.0496   0.9069   0.0306
  -6.500  -0.4205   0.02590   0.02051  -0.0421   0.8980   0.0307
  -6.250  -0.4018   0.02486   0.01909  -0.0397   0.8957   0.0314
  -6.000  -0.3779   0.02249   0.01653  -0.0389   0.8946   0.0324
  -5.750  -0.3462   0.02144   0.01539  -0.0395   0.8936   0.0330
  -5.500  -0.3135   0.02055   0.01443  -0.0402   0.8929   0.0339
  -5.250  -0.3077   0.02040   0.01421  -0.0354   0.8854   0.0350
  -5.000  -0.2801   0.01954   0.01320  -0.0349   0.8833   0.0357
  -4.750  -0.2502   0.01895   0.01243  -0.0348   0.8817   0.0367
  -4.500  -0.2097   0.01746   0.01090  -0.0373   0.8811   0.0379
  -4.250  -0.1713   0.01666   0.01010  -0.0393   0.8801   0.0391
  -4.000  -0.1340   0.01599   0.00942  -0.0410   0.8792   0.0405
  -3.750  -0.0899   0.01513   0.00852  -0.0441   0.8783   0.0416
  -3.500  -0.0449   0.01445   0.00779  -0.0474   0.8771   0.0428
  -3.250  -0.0273   0.01383   0.00716  -0.0449   0.8679   0.0442
  -3.000   0.0178   0.01306   0.00641  -0.0483   0.8642   0.0455
  -2.750   0.0722   0.01231   0.00565  -0.0538   0.8610   0.0482
  -2.500   0.0894   0.01210   0.00541  -0.0511   0.8499   0.0491
  -2.250   0.1459   0.01140   0.00470  -0.0572   0.8451   0.0523
  -2.000   0.1666   0.01123   0.00453  -0.0554   0.8345   0.0546
  -1.750   0.2185   0.01083   0.00409  -0.0606   0.8276   0.0594
  -1.500   0.2408   0.01063   0.00392  -0.0592   0.8168   0.0677
  -1.250   0.2798   0.01003   0.00365  -0.0618   0.8049   0.1602
  -0.750   0.3395   0.00956   0.00340  -0.0626   0.7763   0.2605
  -0.500   0.3630   0.00892   0.00341  -0.0620   0.7575   0.4791
   0.500   0.6944   0.01189   0.00599  -0.1109   0.4383   1.0000
   0.750   0.7084   0.01209   0.00606  -0.1082   0.4204   1.0000
   1.000   0.7243   0.01225   0.00612  -0.1059   0.4064   1.0000
   1.250   0.7404   0.01241   0.00620  -0.1036   0.3939   1.0000
   1.500   0.7561   0.01260   0.00629  -0.1013   0.3800   1.0000
   1.750   0.7732   0.01275   0.00637  -0.0992   0.3664   1.0000
   2.000   0.7905   0.01292   0.00646  -0.0971   0.3526   1.0000
   2.250   0.8078   0.01311   0.00656  -0.0951   0.3376   1.0000
   2.500   0.8249   0.01332   0.00668  -0.0930   0.3207   1.0000
   2.750   0.8420   0.01355   0.00680  -0.0910   0.3048   1.0000
   3.000   0.8590   0.01380   0.00695  -0.0890   0.2895   1.0000
   3.250   0.8756   0.01408   0.00713  -0.0869   0.2744   1.0000
   3.500   0.8922   0.01437   0.00732  -0.0849   0.2635   1.0000
   3.750   0.9103   0.01460   0.00751  -0.0830   0.2554   1.0000
   4.000   0.9265   0.01492   0.00774  -0.0809   0.2475   1.0000
   4.250   0.9453   0.01513   0.00795  -0.0793   0.2421   1.0000
   4.500   0.9633   0.01539   0.00817  -0.0776   0.2366   1.0000
   4.750   0.9800   0.01573   0.00845  -0.0756   0.2312   1.0000
   5.000   0.9989   0.01597   0.00869  -0.0741   0.2274   1.0000
   5.250   1.0179   0.01620   0.00893  -0.0726   0.2246   1.0000
   5.500   1.0357   0.01649   0.00921  -0.0709   0.2209   1.0000
   5.750   1.0527   0.01684   0.00951  -0.0691   0.2174   1.0000
   6.000   1.0688   0.01725   0.00989  -0.0672   0.2137   1.0000
   6.250   1.0882   0.01749   0.01017  -0.0659   0.2121   1.0000
   6.500   1.1072   0.01775   0.01046  -0.0645   0.2098   1.0000
   6.750   1.1257   0.01804   0.01077  -0.0631   0.2074   1.0000
   7.000   1.1435   0.01837   0.01111  -0.0615   0.2057   1.0000
   7.250   1.1607   0.01874   0.01148  -0.0599   0.2034   1.0000
   7.500   1.1777   0.01914   0.01187  -0.0583   0.2012   1.0000
   7.750   1.1945   0.01968   0.01238  -0.0568   0.1982   1.0000
   8.000   1.2132   0.01995   0.01272  -0.0555   0.1970   1.0000
   8.250   1.2316   0.02027   0.01309  -0.0542   0.1957   1.0000
   8.500   1.2497   0.02063   0.01349  -0.0529   0.1944   1.0000
   8.750   1.2675   0.02099   0.01390  -0.0515   0.1928   1.0000
   9.000   1.2853   0.02138   0.01432  -0.0502   0.1913   1.0000
   9.250   1.3024   0.02176   0.01473  -0.0489   0.1893   1.0000
   9.500   1.3201   0.02219   0.01520  -0.0476   0.1885   1.0000
   9.750   1.3371   0.02266   0.01568  -0.0463   0.1870   1.0000
  10.000   1.3542   0.02324   0.01624  -0.0451   0.1841   1.0000
  10.250   1.3708   0.02370   0.01675  -0.0438   0.1820   1.0000
  10.500   1.3869   0.02410   0.01724  -0.0424   0.1807   1.0000
  10.750   1.4011   0.02449   0.01771  -0.0407   0.1783   1.0000
  11.000   1.4164   0.02493   0.01819  -0.0393   0.1762   1.0000
  11.250   1.4324   0.02543   0.01876  -0.0380   0.1752   1.0000
  11.500   1.4459   0.02595   0.01931  -0.0364   0.1727   1.0000
  11.750   1.4602   0.02655   0.01993  -0.0350   0.1708   1.0000
  12.000   1.4759   0.02731   0.02068  -0.0339   0.1681   1.0000
  12.250   1.4891   0.02783   0.02132  -0.0324   0.1670   1.0000
  12.500   1.5013   0.02837   0.02196  -0.0308   0.1647   1.0000
  12.750   1.5154   0.02899   0.02267  -0.0295   0.1634   1.0000
  13.000   1.5275   0.02961   0.02336  -0.0280   0.1607   1.0000
  13.250   1.5393   0.03033   0.02412  -0.0266   0.1586   1.0000
  13.500   1.5503   0.03116   0.02499  -0.0251   0.1565   1.0000
  13.750   1.5605   0.03212   0.02597  -0.0236   0.1540   1.0000
  14.000   1.5726   0.03284   0.02683  -0.0224   0.1523   1.0000
  14.250   1.5844   0.03360   0.02770  -0.0213   0.1491   1.0000
  14.500   1.5957   0.03445   0.02863  -0.0202   0.1462   1.0000
  14.750   1.6032   0.03558   0.02977  -0.0188   0.1423   1.0000
  15.000   1.6125   0.03665   0.03093  -0.0176   0.1394   1.0000
  15.250   1.6256   0.03747   0.03186  -0.0169   0.1346   1.0000
  15.500   1.6309   0.03889   0.03329  -0.0156   0.1290   1.0000
  15.750   1.6404   0.04005   0.03450  -0.0147   0.1197   1.0000
  16.000   1.6390   0.04216   0.03656  -0.0132   0.1053   1.0000
  16.250   1.6244   0.04555   0.03983  -0.0110   0.0857   1.0000
  16.500   1.5881   0.05133   0.04550  -0.0084   0.0625   1.0000
  16.750   1.5657   0.05615   0.05032  -0.0072   0.0506   1.0000
  17.000   1.5380   0.06196   0.05618  -0.0066   0.0406   1.0000
  17.250   1.5245   0.06638   0.06072  -0.0068   0.0375   1.0000
  17.500   1.4930   0.07343   0.06787  -0.0075   0.0319   1.0000
  17.750   1.4606   0.08108   0.07565  -0.0091   0.0285   1.0000
  18.000   1.4414   0.08710   0.08183  -0.0106   0.0281   1.0000
  18.250   1.4070   0.09548   0.09035  -0.0129   0.0263   1.0000
  18.500   1.3802   0.10283   0.09786  -0.0150   0.0259   1.0000
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