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AH-6-40-7 AIRFOIL (ah6407-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: AH-6-40-7 AIRFOIL (ah6407-il)
Reynolds number: 500,000
Max Cl/Cd: 119.73 at α=1.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ah6407-il-500000.txt
Download as CSV file: xf-ah6407-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AH-6-40-7 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3389   0.10172   0.09956  -0.0260   1.0000   0.0170
  -8.000  -0.3510   0.10060   0.09849  -0.0228   1.0000   0.0170
  -7.750  -0.3631   0.09946   0.09739  -0.0197   0.9998   0.0170
  -7.500  -0.3476   0.09360   0.09154  -0.0246   0.9973   0.0173
  -7.250  -0.3305   0.09039   0.08833  -0.0251   0.9961   0.0178
  -7.000  -0.3075   0.08656   0.08448  -0.0301   0.9939   0.0183
  -6.750  -0.2854   0.08267   0.08059  -0.0356   0.9905   0.0189
  -6.500  -0.2593   0.07840   0.07631  -0.0424   0.9874   0.0197
  -6.250  -0.2269   0.07352   0.07140  -0.0515   0.9850   0.0211
  -6.000  -0.1765   0.06705   0.06488  -0.0681   0.9812   0.0224
  -5.750  -0.1387   0.06140   0.05917  -0.0780   0.9773   0.0225
  -5.500  -0.1063   0.05395   0.05167  -0.0875   0.9749   0.0232
  -5.250  -0.0746   0.05119   0.04887  -0.0919   0.9734   0.0241
  -5.000  -0.0349   0.04785   0.04548  -0.0987   0.9722   0.0264
  -4.750   0.0356   0.04052   0.03789  -0.1144   0.9715   0.0298
  -4.500   0.0919   0.03171   0.02868  -0.1263   0.9707   0.0300
  -4.250   0.1434   0.02069   0.01694  -0.1374   0.9697   0.0274
  -4.000   0.1818   0.01758   0.01326  -0.1401   0.9647   0.0292
  -3.750   0.2218   0.01433   0.00941  -0.1433   0.9604   0.0314
  -3.500   0.2534   0.01376   0.00881  -0.1441   0.9541   0.0342
  -3.250   0.2831   0.01293   0.00782  -0.1443   0.9465   0.0363
  -3.000   0.3133   0.01213   0.00683  -0.1445   0.9408   0.0380
  -2.750   0.3408   0.01197   0.00655  -0.1441   0.9325   0.0398
  -2.500   0.3703   0.01072   0.00511  -0.1443   0.9257   0.0415
  -2.250   0.3985   0.00997   0.00428  -0.1442   0.9169   0.0432
  -2.000   0.4263   0.00960   0.00388  -0.1439   0.9078   0.0458
  -1.750   0.4541   0.00927   0.00347  -0.1436   0.8985   0.0478
  -1.500   0.4821   0.00898   0.00313  -0.1434   0.8879   0.0494
  -1.250   0.5103   0.00875   0.00286  -0.1432   0.8775   0.0512
  -1.000   0.5384   0.00858   0.00264  -0.1430   0.8672   0.0530
  -0.750   0.5670   0.00832   0.00232  -0.1429   0.8558   0.0595
  -0.500   0.5952   0.00819   0.00215  -0.1428   0.8434   0.0682
  -0.250   0.6240   0.00786   0.00214  -0.1430   0.8306   0.1756
   0.000   0.6520   0.00778   0.00213  -0.1429   0.8169   0.2282
   0.500   0.7078   0.00754   0.00217  -0.1428   0.7844   0.3842
   0.750   0.7285   0.00632   0.00219  -0.1412   0.7660   1.0000
   1.000   0.7559   0.00645   0.00219  -0.1409   0.7451   1.0000
   1.250   0.7832   0.00660   0.00220  -0.1406   0.7224   1.0000
   1.500   0.8101   0.00678   0.00223  -0.1402   0.6967   1.0000
   1.750   0.8369   0.00699   0.00229  -0.1399   0.6675   1.0000
   2.000   0.8634   0.00724   0.00237  -0.1395   0.6341   1.0000
   2.250   0.8894   0.00755   0.00247  -0.1390   0.5962   1.0000
   2.500   0.9152   0.00790   0.00261  -0.1386   0.5550   1.0000
   2.750   0.9409   0.00827   0.00279  -0.1382   0.5154   1.0000
   3.250   0.9926   0.00900   0.00318  -0.1375   0.4502   1.0000
   3.500   1.0187   0.00933   0.00338  -0.1372   0.4248   1.0000
   3.750   1.0448   0.00965   0.00362  -0.1369   0.4036   1.0000
   4.000   1.0710   0.00996   0.00385  -0.1366   0.3843   1.0000
   4.250   1.0970   0.01027   0.00408  -0.1363   0.3671   1.0000
   4.500   1.1231   0.01057   0.00433  -0.1360   0.3517   1.0000
   4.750   1.1491   0.01087   0.00459  -0.1357   0.3372   1.0000
   5.000   1.1747   0.01120   0.00485  -0.1353   0.3203   1.0000
   5.250   1.2005   0.01149   0.00509  -0.1350   0.3017   1.0000
   5.500   1.2261   0.01179   0.00535  -0.1347   0.2873   1.0000
   5.750   1.2517   0.01209   0.00564  -0.1343   0.2723   1.0000
   6.000   1.2771   0.01241   0.00592  -0.1340   0.2564   1.0000
   6.250   1.3023   0.01273   0.00622  -0.1335   0.2412   1.0000
   6.500   1.3266   0.01315   0.00656  -0.1330   0.2201   1.0000
   6.750   1.3502   0.01366   0.00696  -0.1324   0.1883   1.0000
   7.000   1.3658   0.01522   0.00791  -0.1308   0.0957   1.0000
   7.250   1.3792   0.01710   0.00931  -0.1286   0.0281   1.0000
   7.500   1.3999   0.01797   0.01019  -0.1273   0.0215   1.0000
   7.750   1.4209   0.01872   0.01100  -0.1262   0.0188   1.0000
   8.000   1.4382   0.01989   0.01230  -0.1244   0.0166   1.0000
   8.250   1.4570   0.02079   0.01331  -0.1228   0.0158   1.0000
   8.500   1.4749   0.02170   0.01433  -0.1212   0.0150   1.0000
   8.750   1.4913   0.02270   0.01542  -0.1193   0.0142   1.0000
   9.000   1.5065   0.02372   0.01653  -0.1173   0.0133   1.0000
   9.250   1.5173   0.02506   0.01796  -0.1147   0.0124   1.0000
   9.500   1.5181   0.02712   0.02016  -0.1104   0.0119   1.0000
   9.750   1.5205   0.02891   0.02208  -0.1064   0.0116   1.0000
  10.000   1.5283   0.03007   0.02335  -0.1033   0.0113   1.0000
  10.250   1.5348   0.03142   0.02483  -0.1001   0.0111   1.0000
  10.500   1.5402   0.03300   0.02653  -0.0970   0.0108   1.0000
  10.750   1.5449   0.03474   0.02840  -0.0940   0.0106   1.0000
  11.000   1.5492   0.03662   0.03041  -0.0912   0.0103   1.0000
  11.250   1.5530   0.03866   0.03259  -0.0884   0.0101   1.0000
  11.500   1.5562   0.04084   0.03493  -0.0858   0.0099   1.0000
  11.750   1.5588   0.04306   0.03730  -0.0835   0.0097   1.0000
  12.000   1.5606   0.04531   0.03967  -0.0813   0.0094   1.0000
  12.250   1.5611   0.04772   0.04221  -0.0793   0.0092   1.0000
  12.500   1.5607   0.05021   0.04481  -0.0776   0.0089   1.0000
  12.750   1.5584   0.05313   0.04784  -0.0759   0.0087   1.0000
  13.000   1.5536   0.05665   0.05150  -0.0743   0.0085   1.0000
  13.250   1.5461   0.06069   0.05573  -0.0728   0.0084   1.0000
  13.500   1.5366   0.06498   0.06022  -0.0717   0.0083   1.0000
  13.750   1.5245   0.06975   0.06520  -0.0710   0.0083   1.0000
  14.000   1.5111   0.07473   0.07039  -0.0710   0.0083   1.0000
  14.250   1.4976   0.07990   0.07575  -0.0716   0.0083   1.0000
  14.500   1.4824   0.08558   0.08163  -0.0729   0.0083   1.0000
  14.750   1.4674   0.09152   0.08775  -0.0748   0.0083   1.0000
  15.000   1.4530   0.09773   0.09415  -0.0774   0.0083   1.0000
  15.250   1.4381   0.10444   0.10104  -0.0806   0.0083   1.0000
  15.500   1.4234   0.11148   0.10825  -0.0844   0.0084   1.0000
  15.750   1.4086   0.11888   0.11582  -0.0886   0.0084   1.0000
  16.000   1.3933   0.12680   0.12392  -0.0935   0.0084   1.0000
  16.250   1.3775   0.13547   0.13279  -0.0992   0.0086   1.0000
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