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AH 93-157 (ah93157-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: AH 93-157 (ah93157-il)
Reynolds number: 100,000
Max Cl/Cd: 37.47 at α=9.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ah93157-il-100000-n5.txt
Download as CSV file: xf-ah93157-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AH 93-157                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.2263   0.10107   0.09584  -0.0931   0.9232   0.0345
 -11.750  -0.2260   0.09536   0.09011  -0.0972   0.9170   0.0346
 -11.500  -0.2308   0.08836   0.08309  -0.1023   0.9115   0.0347
 -11.250  -0.2402   0.08115   0.07588  -0.1070   0.9048   0.0348
 -11.000  -0.2572   0.07152   0.06621  -0.1142   0.8983   0.0347
 -10.750  -0.2729   0.06502   0.05962  -0.1193   0.8917   0.0344
 -10.500  -0.2988   0.05947   0.05391  -0.1219   0.8841   0.0342
 -10.250  -0.3213   0.05537   0.04961  -0.1218   0.8775   0.0341
 -10.000  -0.3454   0.05215   0.04619  -0.1192   0.8697   0.0341
  -9.750  -0.3667   0.04929   0.04304  -0.1157   0.8639   0.0342
  -9.500  -0.3821   0.04652   0.03995  -0.1121   0.8580   0.0344
  -9.250  -0.3930   0.04366   0.03667  -0.1085   0.8526   0.0346
  -9.000  -0.3938   0.04113   0.03377  -0.1057   0.8486   0.0350
  -8.750  -0.3870   0.03946   0.03192  -0.1036   0.8441   0.0355
  -8.500  -0.3774   0.03812   0.03042  -0.1017   0.8395   0.0363
  -8.250  -0.3649   0.03689   0.02899  -0.1001   0.8359   0.0375
  -8.000  -0.3515   0.03536   0.02714  -0.0984   0.8328   0.0392
  -7.750  -0.3395   0.03373   0.02512  -0.0963   0.8288   0.0408
  -7.500  -0.3256   0.03217   0.02313  -0.0943   0.8244   0.0420
  -7.250  -0.3063   0.03086   0.02173  -0.0934   0.8210   0.0433
  -7.000  -0.2849   0.02998   0.02073  -0.0927   0.8182   0.0453
  -6.750  -0.2616   0.02903   0.01956  -0.0921   0.8158   0.0484
  -6.500  -0.2437   0.02825   0.01855  -0.0906   0.8111   0.0506
  -6.250  -0.2231   0.02734   0.01764  -0.0897   0.8074   0.0527
  -6.000  -0.2010   0.02672   0.01697  -0.0890   0.8043   0.0561
  -5.750  -0.1762   0.02604   0.01610  -0.0885   0.8017   0.0607
  -5.500  -0.1523   0.02524   0.01531  -0.0880   0.7994   0.0645
  -5.250  -0.1382   0.02505   0.01512  -0.0860   0.7941   0.0693
  -5.000  -0.1187   0.02460   0.01461  -0.0847   0.7903   0.0751
  -4.750  -0.0969   0.02413   0.01413  -0.0838   0.7872   0.0825
  -4.500  -0.0737   0.02361   0.01359  -0.0831   0.7848   0.0922
  -4.250  -0.0570   0.02340   0.01339  -0.0814   0.7807   0.1032
  -4.000  -0.0419   0.02325   0.01328  -0.0794   0.7758   0.1170
  -3.750  -0.0213   0.02287   0.01299  -0.0783   0.7723   0.1389
  -3.500   0.0021   0.02240   0.01266  -0.0777   0.7698   0.1763
  -3.250   0.0261   0.02180   0.01236  -0.0772   0.7678   0.2455
  -3.000   0.0307   0.02178   0.01274  -0.0737   0.7608   0.3255
  -2.750   0.0416   0.02110   0.01271  -0.0708   0.7568   0.4708
  -2.500   0.0995   0.02162   0.01435  -0.0724   0.7561   0.7692
  -2.250   0.1107   0.02193   0.01452  -0.0686   0.7531   0.8158
  -2.000   0.1079   0.02255   0.01507  -0.0629   0.7469   0.8436
  -1.750   0.1279   0.02315   0.01557  -0.0607   0.7423   0.8672
  -1.500   0.1520   0.02345   0.01573  -0.0592   0.7394   0.8887
  -1.250   0.2146   0.02370   0.01579  -0.0648   0.7382   0.9081
  -1.000   0.2983   0.02375   0.01563  -0.0749   0.7376   0.9262
  -0.750   0.3613   0.02358   0.01529  -0.0815   0.7364   0.9387
  -0.500   0.3965   0.02387   0.01553  -0.0837   0.7308   0.9496
  -0.250   0.4239   0.02396   0.01556  -0.0841   0.7263   0.9574
   0.000   0.4601   0.02376   0.01527  -0.0861   0.7234   0.9605
   0.250   0.4956   0.02352   0.01493  -0.0878   0.7211   0.9634
   0.500   0.5113   0.02394   0.01535  -0.0864   0.7143   0.9689
   0.750   0.5380   0.02394   0.01531  -0.0868   0.7098   0.9721
   1.000   0.5718   0.02372   0.01503  -0.0882   0.7070   0.9744
   1.250   0.6058   0.02342   0.01467  -0.0895   0.7047   0.9764
   1.500   0.6158   0.02407   0.01538  -0.0873   0.6959   0.9814
   1.750   0.6451   0.02390   0.01518  -0.0879   0.6923   0.9836
   2.000   0.6795   0.02358   0.01481  -0.0892   0.6899   0.9851
   2.250   0.6939   0.02416   0.01545  -0.0879   0.6813   0.9891
   2.500   0.7219   0.02400   0.01529  -0.0882   0.6773   0.9911
   2.750   0.7548   0.02364   0.01492  -0.0891   0.6746   0.9926
   3.000   0.7673   0.02426   0.01560  -0.0874   0.6657   0.9964
   3.250   0.7966   0.02404   0.01539  -0.0879   0.6617   0.9980
   3.500   0.8310   0.02362   0.01498  -0.0890   0.6590   0.9992
   3.750   0.8249   0.02446   0.01589  -0.0838   0.6488   1.0000
   4.000   0.8514   0.02412   0.01555  -0.0834   0.6452   1.0000
   4.250   0.8426   0.02483   0.01632  -0.0775   0.6358   1.0000
   4.500   0.8642   0.02461   0.01611  -0.0763   0.6311   1.0000
   5.000   0.8723   0.02508   0.01667  -0.0683   0.6169   1.0000
   5.250   0.9068   0.02451   0.01612  -0.0690   0.6136   1.0000
   5.500   0.8686   0.02551   0.01715  -0.0582   0.6019   1.0000
   5.750   0.9061   0.02491   0.01659  -0.0594   0.5986   1.0000
   6.000   0.8674   0.02599   0.01768  -0.0489   0.5865   1.0000
   6.250   0.9053   0.02526   0.01700  -0.0499   0.5832   1.0000
   6.500   0.8745   0.02638   0.01814  -0.0412   0.5711   1.0000
   7.000   0.8917   0.02664   0.01846  -0.0353   0.5554   1.0000
   7.500   0.9205   0.02681   0.01873  -0.0312   0.5395   1.0000
   7.750   0.9263   0.02746   0.01943  -0.0286   0.5293   1.0000
   8.000   0.9585   0.02690   0.01892  -0.0287   0.5231   1.0000
   8.250   0.9647   0.02768   0.01978  -0.0263   0.5118   1.0000
   8.500   0.9905   0.02749   0.01964  -0.0259   0.5035   1.0000
   8.750   1.0088   0.02773   0.01994  -0.0248   0.4932   1.0000
   9.000   1.0212   0.02834   0.02062  -0.0232   0.4817   1.0000
   9.250   1.0434   0.02843   0.02077  -0.0225   0.4715   1.0000
   9.500   1.0668   0.02847   0.02085  -0.0220   0.4608   1.0000
   9.750   1.0775   0.02925   0.02170  -0.0204   0.4481   1.0000
  10.000   1.0912   0.02988   0.02238  -0.0191   0.4352   1.0000
  10.250   1.1059   0.03046   0.02303  -0.0179   0.4220   1.0000
  10.500   1.1203   0.03108   0.02368  -0.0167   0.4085   1.0000
  10.750   1.1334   0.03179   0.02442  -0.0154   0.3946   1.0000
  11.000   1.1412   0.03280   0.02545  -0.0137   0.3782   1.0000
  11.250   1.1459   0.03402   0.02668  -0.0119   0.3599   1.0000
  11.500   1.1496   0.03534   0.02796  -0.0101   0.3403   1.0000
  11.750   1.1527   0.03677   0.02933  -0.0084   0.3208   1.0000
  12.000   1.1537   0.03849   0.03107  -0.0068   0.3021   1.0000
  12.250   1.1552   0.04027   0.03284  -0.0054   0.2832   1.0000
  12.500   1.1559   0.04218   0.03472  -0.0040   0.2642   1.0000
  13.000   1.1548   0.04655   0.03905  -0.0017   0.2250   1.0000
  13.250   1.1522   0.04907   0.04154  -0.0007   0.2045   1.0000
  13.500   1.1484   0.05183   0.04424   0.0002   0.1837   1.0000
  13.750   1.1436   0.05484   0.04720   0.0009   0.1622   1.0000
  14.000   1.1377   0.05808   0.05037   0.0014   0.1421   1.0000
  14.250   1.1304   0.06162   0.05383   0.0017   0.1214   1.0000
  14.500   1.1227   0.06534   0.05748   0.0018   0.1049   1.0000
  14.750   1.1158   0.06911   0.06121   0.0017   0.0903   1.0000
  15.000   1.1086   0.07305   0.06512   0.0015   0.0783   1.0000
  15.250   1.1020   0.07704   0.06911   0.0010   0.0693   1.0000
  15.500   1.0968   0.08096   0.07308   0.0005   0.0620   1.0000
  15.750   1.0896   0.08522   0.07736  -0.0003   0.0569   1.0000
  16.000   1.0863   0.08906   0.08131  -0.0010   0.0518   1.0000
  16.250   1.0806   0.09328   0.08557  -0.0020   0.0487   1.0000
  16.500   1.0784   0.09705   0.08943  -0.0029   0.0452   1.0000
  16.750   1.0758   0.10094   0.09341  -0.0040   0.0421   1.0000
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