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AH 93-157 (ah93157-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: AH 93-157 (ah93157-il)
Reynolds number: 500,000
Max Cl/Cd: 100.41 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ah93157-il-500000.txt
Download as CSV file: xf-ah93157-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.1284   0.10197   0.09899  -0.0890   0.8240   0.0296
 -12.500  -0.3908   0.05331   0.04999  -0.1263   0.8428   0.0191
 -12.250  -0.4233   0.04738   0.04388  -0.1289   0.8374   0.0190
 -12.000  -0.4540   0.04305   0.03930  -0.1283   0.8325   0.0190
 -11.750  -0.4791   0.03975   0.03580  -0.1257   0.8279   0.0190
 -11.500  -0.5010   0.03688   0.03270  -0.1221   0.8234   0.0190
 -11.250  -0.5189   0.03459   0.03014  -0.1177   0.8193   0.0191
 -11.000  -0.5338   0.03263   0.02790  -0.1128   0.8155   0.0192
 -10.750  -0.5402   0.03137   0.02641  -0.1084   0.8120   0.0193
 -10.500  -0.5498   0.02812   0.02284  -0.1042   0.8084   0.0196
 -10.250  -0.5425   0.02636   0.02089  -0.1019   0.8053   0.0198
 -10.000  -0.5279   0.02551   0.01996  -0.1004   0.8028   0.0203
  -9.750  -0.5126   0.02469   0.01901  -0.0989   0.8003   0.0208
  -9.500  -0.4957   0.02393   0.01816  -0.0975   0.7977   0.0214
  -9.250  -0.4792   0.02282   0.01688  -0.0960   0.7949   0.0220
  -9.000  -0.4608   0.02193   0.01581  -0.0948   0.7921   0.0227
  -8.750  -0.4408   0.02137   0.01507  -0.0937   0.7895   0.0234
  -8.500  -0.4211   0.01978   0.01330  -0.0928   0.7872   0.0243
  -8.250  -0.3990   0.01902   0.01247  -0.0922   0.7849   0.0249
  -8.000  -0.3765   0.01850   0.01191  -0.0915   0.7825   0.0258
  -7.750  -0.3538   0.01792   0.01126  -0.0908   0.7801   0.0267
  -7.500  -0.3304   0.01736   0.01062  -0.0902   0.7776   0.0277
  -7.250  -0.3063   0.01704   0.01020  -0.0897   0.7750   0.0287
  -7.000  -0.2842   0.01602   0.00915  -0.0890   0.7726   0.0302
  -6.750  -0.2602   0.01563   0.00873  -0.0885   0.7704   0.0317
  -6.500  -0.2359   0.01526   0.00829  -0.0881   0.7682   0.0332
  -6.250  -0.2117   0.01496   0.00794  -0.0875   0.7659   0.0346
  -6.000  -0.1907   0.01428   0.00727  -0.0865   0.7632   0.0368
  -5.750  -0.1665   0.01400   0.00699  -0.0860   0.7605   0.0394
  -5.500  -0.1415   0.01375   0.00669  -0.0856   0.7581   0.0418
  -5.250  -0.1191   0.01323   0.00616  -0.0848   0.7557   0.0453
  -5.000  -0.0936   0.01301   0.00590  -0.0845   0.7535   0.0492
  -4.750  -0.0697   0.01271   0.00559  -0.0839   0.7513   0.0545
  -4.500  -0.0453   0.01250   0.00539  -0.0834   0.7487   0.0602
  -4.250  -0.0217   0.01218   0.00512  -0.0828   0.7458   0.0686
  -4.000   0.0029   0.01192   0.00490  -0.0823   0.7432   0.0799
  -3.750   0.0278   0.01165   0.00468  -0.0819   0.7407   0.0967
  -3.500   0.0526   0.01136   0.00448  -0.0816   0.7384   0.1241
  -3.250   0.0770   0.01107   0.00433  -0.0812   0.7361   0.1683
  -3.000   0.0986   0.01068   0.00422  -0.0803   0.7334   0.2360
  -2.750   0.1188   0.01019   0.00410  -0.0793   0.7301   0.3314
  -2.500   0.1368   0.00955   0.00394  -0.0778   0.7271   0.4610
  -2.250   0.1481   0.00859   0.00377  -0.0748   0.7244   0.6672
  -2.000   0.1687   0.00867   0.00428  -0.0725   0.7221   0.7984
  -1.750   0.1955   0.00895   0.00450  -0.0720   0.7196   0.8275
  -1.500   0.2203   0.00920   0.00473  -0.0711   0.7164   0.8435
  -1.250   0.2462   0.00952   0.00504  -0.0702   0.7133   0.8526
  -1.000   0.2725   0.00971   0.00518  -0.0697   0.7102   0.8616
  -0.750   0.2993   0.00995   0.00537  -0.0690   0.7075   0.8685
  -0.500   0.3259   0.01016   0.00551  -0.0684   0.7049   0.8767
  -0.250   0.3499   0.01036   0.00572  -0.0672   0.7015   0.8825
   0.000   0.3735   0.01047   0.00582  -0.0662   0.6977   0.8906
   0.250   0.3992   0.01065   0.00599  -0.0650   0.6944   0.8981
   0.500   0.4255   0.01078   0.00608  -0.0640   0.6915   0.9076
   0.750   0.4510   0.01095   0.00621  -0.0632   0.6883   0.9171
   1.000   0.4831   0.01093   0.00621  -0.0637   0.6841   0.9220
   1.250   0.5127   0.01089   0.00615  -0.0641   0.6802   0.9256
   1.500   0.5339   0.01080   0.00602  -0.0629   0.6766   0.9293
   1.750   0.5554   0.01072   0.00589  -0.0619   0.6731   0.9323
   2.000   0.5816   0.01060   0.00581  -0.0617   0.6683   0.9338
   2.250   0.6097   0.01051   0.00570  -0.0620   0.6637   0.9354
   2.500   0.6378   0.01044   0.00558  -0.0622   0.6598   0.9369
   2.750   0.6603   0.01038   0.00553  -0.0614   0.6550   0.9390
   3.000   0.6805   0.01030   0.00546  -0.0601   0.6498   0.9418
   3.250   0.7009   0.01022   0.00536  -0.0588   0.6453   0.9441
   3.500   0.7233   0.01014   0.00528  -0.0579   0.6398   0.9458
   3.750   0.7485   0.01006   0.00522  -0.0576   0.6340   0.9473
   4.000   0.7753   0.01001   0.00514  -0.0577   0.6290   0.9485
   4.250   0.7974   0.00997   0.00514  -0.0568   0.6223   0.9502
   4.500   0.8209   0.00993   0.00509  -0.0561   0.6159   0.9521
   4.750   0.8424   0.00991   0.00509  -0.0551   0.6094   0.9538
   5.000   0.8622   0.00987   0.00506  -0.0538   0.6021   0.9556
   5.250   0.8826   0.00987   0.00506  -0.0526   0.5952   0.9573
   5.500   0.9038   0.00985   0.00506  -0.0516   0.5872   0.9589
   5.750   0.9267   0.00987   0.00508  -0.0509   0.5793   0.9602
   6.000   0.9483   0.00990   0.00512  -0.0500   0.5704   0.9616
   6.250   0.9688   0.00995   0.00518  -0.0489   0.5609   0.9632
   6.500   0.9887   0.01003   0.00525  -0.0477   0.5516   0.9652
   6.750   1.0057   0.01010   0.00534  -0.0459   0.5409   0.9672
   7.000   1.0206   0.01018   0.00543  -0.0437   0.5310   0.9693
   7.250   1.0362   0.01032   0.00555  -0.0418   0.5205   0.9712
   7.500   1.0549   0.01053   0.00577  -0.0406   0.5076   0.9732
   7.750   1.0745   0.01081   0.00605  -0.0397   0.4939   0.9755
   8.000   1.0944   0.01112   0.00637  -0.0389   0.4808   0.9776
   8.250   1.1132   0.01151   0.00676  -0.0381   0.4658   0.9797
   8.500   1.1303   0.01205   0.00725  -0.0373   0.4475   0.9821
   8.750   1.1479   0.01278   0.00792  -0.0369   0.4242   0.9847
   9.000   1.1646   0.01364   0.00871  -0.0366   0.4005   0.9880
   9.250   1.1817   0.01448   0.00950  -0.0364   0.3804   0.9935
   9.500   1.1897   0.01536   0.01034  -0.0344   0.3626   1.0000
   9.750   1.1935   0.01620   0.01114  -0.0315   0.3468   1.0000
  10.000   1.1983   0.01718   0.01207  -0.0291   0.3286   1.0000
  10.250   1.2031   0.01829   0.01310  -0.0268   0.3095   1.0000
  10.500   1.2091   0.01943   0.01419  -0.0249   0.2919   1.0000
  10.750   1.2152   0.02063   0.01533  -0.0230   0.2729   1.0000
  11.000   1.2212   0.02188   0.01651  -0.0213   0.2534   1.0000
  11.250   1.2251   0.02330   0.01785  -0.0194   0.2324   1.0000
  11.500   1.2286   0.02480   0.01925  -0.0177   0.2107   1.0000
  11.750   1.2310   0.02644   0.02079  -0.0159   0.1884   1.0000
  12.000   1.2327   0.02818   0.02242  -0.0142   0.1648   1.0000
  12.250   1.2323   0.03013   0.02424  -0.0125   0.1396   1.0000
  12.500   1.2309   0.03225   0.02622  -0.0108   0.1152   1.0000
  12.750   1.2283   0.03453   0.02836  -0.0092   0.0916   1.0000
  13.000   1.2259   0.03689   0.03059  -0.0077   0.0697   1.0000
  13.250   1.2248   0.03923   0.03284  -0.0065   0.0538   1.0000
  13.500   1.2255   0.04149   0.03506  -0.0055   0.0436   1.0000
  13.750   1.2268   0.04379   0.03734  -0.0046   0.0366   1.0000
  14.000   1.2273   0.04623   0.03979  -0.0038   0.0320   1.0000
  14.250   1.2311   0.04840   0.04202  -0.0032   0.0286   1.0000
  14.500   1.2308   0.05104   0.04469  -0.0026   0.0259   1.0000
  14.750   1.2356   0.05325   0.04697  -0.0023   0.0238   1.0000
  15.000   1.2365   0.05589   0.04966  -0.0020   0.0224   1.0000
  15.250   1.2332   0.05904   0.05288  -0.0017   0.0211   1.0000
  15.500   1.2367   0.06154   0.05547  -0.0016   0.0199   1.0000
  15.750   1.2401   0.06408   0.05806  -0.0017   0.0186   1.0000
  16.000   1.2381   0.06730   0.06134  -0.0017   0.0179   1.0000
  16.250   1.2308   0.07119   0.06530  -0.0019   0.0171   1.0000
  16.500   1.2336   0.07395   0.06817  -0.0022   0.0165   1.0000
  16.750   1.2333   0.07716   0.07147  -0.0026   0.0159   1.0000
  17.000   1.2336   0.08034   0.07473  -0.0031   0.0153   1.0000
  17.250   1.2320   0.08380   0.07826  -0.0037   0.0149   1.0000
  17.500   1.2301   0.08734   0.08187  -0.0044   0.0144   1.0000
  17.750   1.2243   0.09141   0.08600  -0.0053   0.0140   1.0000
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