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AH 83-150 Q (ah83150q-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: AH 83-150 Q (ah83150q-il)
Reynolds number: 500,000
Max Cl/Cd: 109.73 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ah83150q-il-500000.txt
Download as CSV file: xf-ah83150q-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AH 83-150 Q                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.1718   0.08479   0.08162  -0.0560   0.7142   0.0162
  -9.750  -0.1781   0.07867   0.07551  -0.0596   0.7131   0.0163
  -9.500  -0.1816   0.07348   0.07035  -0.0615   0.7116   0.0164
  -9.250  -0.1839   0.06850   0.06538  -0.0641   0.7101   0.0164
  -9.000  -0.1789   0.06629   0.06317  -0.0636   0.7080   0.0168
  -8.750  -0.1810   0.06198   0.05886  -0.0657   0.7063   0.0169
  -8.500  -0.1827   0.05819   0.05507  -0.0676   0.7047   0.0173
  -8.250  -0.2710   0.05992   0.05644  -0.0798   0.7081   0.0162
  -8.000  -0.2914   0.05482   0.05114  -0.0790   0.7060   0.0164
  -7.750  -0.2888   0.05201   0.04827  -0.0786   0.7040   0.0166
  -7.500  -0.2837   0.04970   0.04589  -0.0781   0.7021   0.0167
  -7.250  -0.2746   0.04800   0.04416  -0.0778   0.7003   0.0171
  -7.000  -0.2656   0.04545   0.04151  -0.0773   0.6985   0.0174
  -6.750  -0.2546   0.04293   0.03886  -0.0768   0.6964   0.0181
  -6.500  -0.2440   0.03986   0.03513  -0.0743   0.6943   0.0204
  -6.250  -0.2343   0.03535   0.03054  -0.0739   0.6924   0.0210
  -6.000  -0.2158   0.03354   0.02867  -0.0738   0.6904   0.0215
  -5.750  -0.1959   0.03210   0.02712  -0.0735   0.6886   0.0225
  -5.500  -0.1727   0.03258   0.02694  -0.0716   0.6869   0.0255
  -5.250  -0.1561   0.02792   0.02234  -0.0719   0.6851   0.0268
  -5.000  -0.1327   0.02655   0.02092  -0.0718   0.6832   0.0280
  -4.750  -0.1051   0.02753   0.02149  -0.0709   0.6810   0.0317
  -4.500  -0.0849   0.02345   0.01736  -0.0709   0.6792   0.0336
  -4.250  -0.0593   0.02238   0.01620  -0.0709   0.6772   0.0358
  -3.750  -0.0071   0.02010   0.01363  -0.0706   0.6734   0.0441
  -3.500   0.0269   0.01597   0.00869  -0.0678   0.6719   0.0166
  -3.250   0.0539   0.01519   0.00788  -0.0675   0.6701   0.0159
  -3.000   0.0801   0.01437   0.00706  -0.0672   0.6684   0.0155
  -2.750   0.1061   0.01369   0.00637  -0.0669   0.6664   0.0154
  -2.500   0.1324   0.01317   0.00584  -0.0667   0.6642   0.0155
  -2.250   0.1594   0.01277   0.00541  -0.0666   0.6620   0.0162
  -2.000   0.1860   0.01231   0.00492  -0.0665   0.6600   0.0172
  -1.750   0.2137   0.01204   0.00462  -0.0665   0.6581   0.0192
  -1.500   0.2416   0.01183   0.00437  -0.0666   0.6562   0.0231
  -1.250   0.2672   0.01116   0.00411  -0.0666   0.6542   0.1499
  -1.000   0.2795   0.00920   0.00435  -0.0647   0.6522   0.7704
  -0.750   0.3046   0.00979   0.00497  -0.0634   0.6496   0.8164
  -0.500   0.3246   0.01045   0.00569  -0.0604   0.6471   0.8395
  -0.250   0.3444   0.01091   0.00616  -0.0576   0.6448   0.8586
   0.000   0.3638   0.01110   0.00634  -0.0550   0.6426   0.8709
   0.250   0.3879   0.01113   0.00631  -0.0538   0.6405   0.8781
   0.500   0.4134   0.01121   0.00633  -0.0532   0.6383   0.8829
   0.750   0.4417   0.01119   0.00630  -0.0536   0.6357   0.8857
   1.000   0.4714   0.01116   0.00625  -0.0543   0.6328   0.8875
   1.250   0.5016   0.01114   0.00618  -0.0551   0.6301   0.8888
   1.500   0.5296   0.01102   0.00603  -0.0553   0.6275   0.8899
   1.750   0.5581   0.01096   0.00591  -0.0555   0.6252   0.8911
   2.000   0.5868   0.01096   0.00587  -0.0559   0.6226   0.8921
   2.250   0.6148   0.01090   0.00585  -0.0563   0.6192   0.8931
   2.500   0.6432   0.01085   0.00580  -0.0566   0.6158   0.8944
   2.750   0.6722   0.01079   0.00572  -0.0571   0.6127   0.8956
   3.000   0.7019   0.01075   0.00563  -0.0577   0.6099   0.8965
   3.250   0.7310   0.01076   0.00564  -0.0582   0.6068   0.8974
   3.500   0.7596   0.01073   0.00565  -0.0587   0.6029   0.8985
   3.750   0.7887   0.01069   0.00562  -0.0593   0.5991   0.8997
   4.000   0.8184   0.01066   0.00556  -0.0599   0.5958   0.9006
   4.250   0.8480   0.01067   0.00557  -0.0606   0.5922   0.9014
   4.500   0.8765   0.01066   0.00561  -0.0611   0.5875   0.9021
   4.750   0.9059   0.01063   0.00559  -0.0618   0.5830   0.9028
   5.000   0.9343   0.01057   0.00550  -0.0621   0.5789   0.9036
   5.250   0.9606   0.01050   0.00553  -0.0621   0.5723   0.9047
   5.500   0.9880   0.01041   0.00542  -0.0622   0.5651   0.9057
   5.750   1.0147   0.01037   0.00544  -0.0624   0.5562   0.9066
   6.000   1.0421   0.01038   0.00543  -0.0626   0.5495   0.9074
   6.250   1.0691   0.01041   0.00554  -0.0628   0.5417   0.9083
   6.500   1.0959   0.01046   0.00557  -0.0630   0.5338   0.9091
   6.750   1.1223   0.01052   0.00570  -0.0631   0.5241   0.9101
   7.000   1.1482   0.01062   0.00582  -0.0632   0.5146   0.9113
   7.250   1.1732   0.01075   0.00595  -0.0631   0.5032   0.9125
   7.500   1.1976   0.01092   0.00613  -0.0629   0.4901   0.9135
   7.750   1.2213   0.01113   0.00634  -0.0627   0.4761   0.9145
   8.000   1.2435   0.01141   0.00660  -0.0622   0.4604   0.9155
   8.250   1.2641   0.01175   0.00692  -0.0615   0.4410   0.9165
   8.500   1.2796   0.01221   0.00730  -0.0600   0.4178   0.9177
   8.750   1.2904   0.01275   0.00776  -0.0576   0.3923   0.9196
   9.000   1.2949   0.01337   0.00830  -0.0543   0.3701   0.9220
   9.250   1.2995   0.01405   0.00893  -0.0511   0.3507   0.9242
   9.500   1.3036   0.01489   0.00975  -0.0483   0.3324   0.9266
   9.750   1.3058   0.01598   0.01078  -0.0456   0.3135   0.9291
  10.000   1.3083   0.01723   0.01198  -0.0433   0.2959   0.9315
  10.250   1.3116   0.01850   0.01323  -0.0413   0.2781   0.9346
  10.500   1.3141   0.01992   0.01462  -0.0393   0.2597   0.9385
  10.750   1.3165   0.02145   0.01610  -0.0375   0.2415   0.9423
  11.000   1.3182   0.02315   0.01776  -0.0359   0.2231   0.9467
  11.250   1.3229   0.02488   0.01945  -0.0350   0.2047   0.9529
  11.750   1.3345   0.02863   0.02310  -0.0342   0.1689   1.0000
  12.000   1.3395   0.03038   0.02483  -0.0334   0.1565   1.0000
  12.250   1.3427   0.03230   0.02669  -0.0325   0.1428   1.0000
  12.500   1.3489   0.03403   0.02843  -0.0319   0.1342   1.0000
  13.000   1.3598   0.03777   0.03213  -0.0307   0.1141   1.0000
  13.250   1.3662   0.03964   0.03400  -0.0303   0.1050   1.0000
  13.500   1.3706   0.04171   0.03606  -0.0298   0.0960   1.0000
  13.750   1.3755   0.04380   0.03812  -0.0294   0.0862   1.0000
  14.000   1.3795   0.04603   0.04034  -0.0291   0.0762   1.0000
  14.250   1.3828   0.04835   0.04265  -0.0288   0.0671   1.0000
  14.500   1.3851   0.05084   0.04513  -0.0286   0.0599   1.0000
  14.750   1.3871   0.05342   0.04771  -0.0285   0.0547   1.0000
  15.000   1.3913   0.05583   0.05017  -0.0285   0.0504   1.0000
  15.250   1.3944   0.05840   0.05279  -0.0285   0.0473   1.0000
  15.500   1.3943   0.06139   0.05580  -0.0286   0.0441   1.0000
  15.750   1.3985   0.06397   0.05846  -0.0288   0.0422   1.0000
  16.000   1.4034   0.06647   0.06104  -0.0291   0.0400   1.0000
  16.250   1.4054   0.06937   0.06399  -0.0295   0.0379   1.0000
  16.500   1.4034   0.07283   0.06750  -0.0300   0.0356   1.0000
  16.750   1.4086   0.07541   0.07017  -0.0305   0.0340   1.0000
  17.000   1.4122   0.07826   0.07312  -0.0311   0.0327   1.0000
  17.250   1.4145   0.08131   0.07624  -0.0318   0.0310   1.0000
  17.500   1.4128   0.08496   0.07993  -0.0326   0.0290   1.0000
  17.750   1.4139   0.08827   0.08333  -0.0335   0.0276   1.0000
  18.000   1.4185   0.09111   0.08627  -0.0344   0.0257   1.0000
  18.250   1.4174   0.09482   0.09002  -0.0356   0.0233   1.0000
  18.500   1.4183   0.09829   0.09358  -0.0367   0.0203   1.0000
  18.750   1.4147   0.10250   0.09782  -0.0381   0.0163   1.0000
  19.000   1.4093   0.10701   0.10238  -0.0398   0.0138   1.0000
  19.250   1.4005   0.11217   0.10759  -0.0417   0.0107   1.0000
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