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AH 94-156 (ah94156-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: AH 94-156 (ah94156-il)
Reynolds number: 100,000
Max Cl/Cd: 36.26 at α=10°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ah94156-il-100000-n5.txt
Download as CSV file: xf-ah94156-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AH 94-156                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.2204   0.09348   0.08819  -0.0966   0.8841   0.0293
 -11.000  -0.2210   0.08903   0.08375  -0.0987   0.8800   0.0291
 -10.750  -0.2201   0.08526   0.07999  -0.1004   0.8755   0.0288
 -10.500  -0.2218   0.08088   0.07562  -0.1028   0.8713   0.0285
 -10.250  -0.2335   0.07367   0.06840  -0.1077   0.8676   0.0282
 -10.000  -0.2480   0.06759   0.06228  -0.1121   0.8628   0.0278
  -9.750  -0.2670   0.06274   0.05734  -0.1142   0.8577   0.0274
  -9.500  -0.2881   0.05859   0.05302  -0.1142   0.8530   0.0273
  -9.250  -0.3061   0.05547   0.04975  -0.1128   0.8475   0.0270
  -9.000  -0.3242   0.05290   0.04700  -0.1098   0.8425   0.0269
  -8.750  -0.3363   0.05001   0.04382  -0.1070   0.8388   0.0270
  -8.500  -0.3428   0.04736   0.04086  -0.1043   0.8350   0.0273
  -8.250  -0.3464   0.04480   0.03795  -0.1016   0.8303   0.0278
  -8.000  -0.3460   0.04225   0.03496  -0.0988   0.8265   0.0284
  -7.750  -0.3418   0.03984   0.03199  -0.0961   0.8235   0.0292
  -7.500  -0.3315   0.03771   0.02947  -0.0941   0.8208   0.0296
  -7.250  -0.3190   0.03592   0.02747  -0.0926   0.8168   0.0300
  -7.000  -0.3031   0.03436   0.02569  -0.0912   0.8133   0.0307
  -6.750  -0.2842   0.03291   0.02401  -0.0902   0.8105   0.0314
  -6.500  -0.2629   0.03153   0.02237  -0.0893   0.8083   0.0324
  -6.250  -0.2401   0.03040   0.02101  -0.0886   0.8065   0.0343
  -6.000  -0.2219   0.02966   0.02003  -0.0873   0.8023   0.0365
  -5.750  -0.2007   0.02855   0.01886  -0.0865   0.7989   0.0382
  -5.500  -0.1784   0.02765   0.01791  -0.0858   0.7961   0.0400
  -5.250  -0.1552   0.02687   0.01704  -0.0851   0.7939   0.0426
  -5.000  -0.1312   0.02623   0.01625  -0.0845   0.7920   0.0466
  -4.750  -0.1161   0.02574   0.01582  -0.0828   0.7881   0.0500
  -4.500  -0.1003   0.02539   0.01543  -0.0811   0.7839   0.0540
  -4.250  -0.0816   0.02492   0.01491  -0.0797   0.7809   0.0606
  -4.000  -0.0602   0.02447   0.01440  -0.0787   0.7785   0.0704
  -3.750  -0.0382   0.02385   0.01385  -0.0778   0.7766   0.0881
  -3.500  -0.0273   0.02372   0.01390  -0.0755   0.7715   0.1173
  -3.250  -0.0137   0.02323   0.01384  -0.0736   0.7675   0.1994
  -3.000  -0.0007   0.02227   0.01370  -0.0715   0.7645   0.3753
  -2.750   0.0109   0.02142   0.01400  -0.0675   0.7623   0.6171
  -2.500   0.0524   0.02274   0.01565  -0.0660   0.7614   0.7811
  -2.250   0.0413   0.02356   0.01643  -0.0594   0.7541   0.8171
  -2.000   0.0546   0.02418   0.01692  -0.0558   0.7503   0.8492
  -1.750   0.0784   0.02458   0.01716  -0.0539   0.7480   0.8742
  -1.500   0.1255   0.02488   0.01727  -0.0563   0.7469   0.8936
  -1.250   0.1785   0.02499   0.01718  -0.0603   0.7460   0.9087
  -1.000   0.2036   0.02551   0.01762  -0.0606   0.7402   0.9206
  -0.750   0.2347   0.02565   0.01763  -0.0616   0.7366   0.9302
  -0.500   0.2838   0.02555   0.01739  -0.0660   0.7346   0.9345
  -0.250   0.3171   0.02542   0.01713  -0.0672   0.7324   0.9410
   0.000   0.3580   0.02518   0.01677  -0.0698   0.7308   0.9447
   0.250   0.3767   0.02577   0.01735  -0.0695   0.7236   0.9512
   0.500   0.4015   0.02577   0.01728  -0.0694   0.7197   0.9566
   0.750   0.4408   0.02556   0.01698  -0.0718   0.7176   0.9590
   1.000   0.4791   0.02525   0.01660  -0.0739   0.7158   0.9615
   1.250   0.4868   0.02602   0.01739  -0.0717   0.7071   0.9681
   1.500   0.5181   0.02588   0.01721  -0.0726   0.7039   0.9709
   1.750   0.5545   0.02560   0.01689  -0.0744   0.7018   0.9727
   2.250   0.5962   0.02619   0.01749  -0.0736   0.6898   0.9804
   2.500   0.6271   0.02590   0.01719  -0.0742   0.6873   0.9826
   2.750   0.6639   0.02550   0.01677  -0.0759   0.6855   0.9838
   3.000   0.6716   0.02643   0.01777  -0.0740   0.6751   0.9885
   3.250   0.7044   0.02608   0.01743  -0.0749   0.6725   0.9902
   3.500   0.7370   0.02574   0.01711  -0.0758   0.6700   0.9917
   3.750   0.7422   0.02662   0.01805  -0.0733   0.6596   0.9963
   4.000   0.7761   0.02618   0.01764  -0.0743   0.6571   0.9975
   4.500   0.7943   0.02674   0.01830  -0.0688   0.6432   1.0000
   5.000   0.7888   0.02723   0.01883  -0.0587   0.6283   1.0000
   5.500   0.7886   0.02764   0.01930  -0.0499   0.6132   1.0000
   6.000   0.7959   0.02793   0.01967  -0.0423   0.5982   1.0000
   6.250   0.7820   0.02883   0.02058  -0.0366   0.5862   1.0000
   6.500   0.8122   0.02807   0.01988  -0.0363   0.5833   1.0000
   6.750   0.8081   0.02896   0.02080  -0.0324   0.5714   1.0000
   7.000   0.8415   0.02814   0.02007  -0.0325   0.5683   1.0000
   7.500   0.8620   0.02921   0.02126  -0.0287   0.5479   1.0000
   7.750   0.8883   0.02888   0.02100  -0.0283   0.5409   1.0000
   8.250   0.9378   0.02857   0.02085  -0.0274   0.5246   1.0000
   8.500   0.9519   0.02914   0.02151  -0.0262   0.5131   1.0000
   8.750   0.9755   0.02912   0.02157  -0.0257   0.5032   1.0000
   9.000   1.0076   0.02858   0.02111  -0.0259   0.4942   1.0000
   9.250   1.0245   0.02904   0.02165  -0.0250   0.4815   1.0000
   9.500   1.0440   0.02935   0.02204  -0.0242   0.4690   1.0000
   9.750   1.0650   0.02958   0.02235  -0.0236   0.4558   1.0000
  10.000   1.0841   0.02990   0.02271  -0.0228   0.4407   1.0000
  10.250   1.1006   0.03036   0.02320  -0.0217   0.4234   1.0000
  10.500   1.1157   0.03092   0.02374  -0.0206   0.4049   1.0000
  10.750   1.1256   0.03186   0.02468  -0.0192   0.3859   1.0000
  11.000   1.1324   0.03306   0.02592  -0.0176   0.3660   1.0000
  11.250   1.1394   0.03426   0.02709  -0.0161   0.3455   1.0000
  11.500   1.1440   0.03569   0.02852  -0.0146   0.3242   1.0000
  11.750   1.1471   0.03729   0.03009  -0.0131   0.3019   1.0000
  12.000   1.1489   0.03907   0.03182  -0.0117   0.2786   1.0000
  12.250   1.1492   0.04105   0.03373  -0.0103   0.2546   1.0000
  12.500   1.1480   0.04329   0.03590  -0.0090   0.2290   1.0000
  12.750   1.1461   0.04571   0.03824  -0.0079   0.2040   1.0000
  13.000   1.1424   0.04841   0.04085  -0.0069   0.1790   1.0000
  13.250   1.1378   0.05135   0.04368  -0.0061   0.1542   1.0000
  13.500   1.1333   0.05441   0.04666  -0.0054   0.1304   1.0000
  13.750   1.1286   0.05763   0.04979  -0.0050   0.1107   1.0000
  14.000   1.1236   0.06100   0.05309  -0.0047   0.0931   1.0000
  14.250   1.1190   0.06447   0.05652  -0.0046   0.0795   1.0000
  14.500   1.1146   0.06802   0.06006  -0.0046   0.0684   1.0000
  14.750   1.1105   0.07163   0.06371  -0.0048   0.0606   1.0000
  15.000   1.1060   0.07542   0.06752  -0.0052   0.0542   1.0000
  15.250   1.1035   0.07904   0.07123  -0.0056   0.0485   1.0000
  15.500   1.0989   0.08303   0.07526  -0.0063   0.0444   1.0000
  15.750   1.0967   0.08673   0.07908  -0.0070   0.0413   1.0000
  16.000   1.0952   0.09043   0.08290  -0.0078   0.0378   1.0000
  16.250   1.0911   0.09455   0.08706  -0.0088   0.0353   1.0000
  16.500   1.0916   0.09798   0.09060  -0.0096   0.0333   1.0000
  16.750   1.0934   0.10124   0.09399  -0.0104   0.0313   1.0000
  17.000   1.0937   0.10479   0.09763  -0.0114   0.0294   1.0000
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