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AH 93-156 (ah93156-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: AH 93-156 (ah93156-il)
Reynolds number: 50,000
Max Cl/Cd: 15.61 at α=12°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ah93156-il-50000-n5.txt
Download as CSV file: xf-ah93156-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AH 93-156                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.2521   0.11605   0.10923  -0.0792   0.9578   0.0645
 -11.250  -0.2469   0.11142   0.10459  -0.0827   0.9541   0.0637
 -11.000  -0.2440   0.10699   0.10017  -0.0859   0.9496   0.0635
 -10.750  -0.2404   0.10232   0.09549  -0.0896   0.9458   0.0635
 -10.500  -0.2374   0.09722   0.09039  -0.0940   0.9425   0.0638
 -10.250  -0.2401   0.09254   0.08572  -0.0973   0.9374   0.0634
 -10.000  -0.2462   0.08710   0.08029  -0.1014   0.9321   0.0630
  -9.750  -0.2567   0.08016   0.07332  -0.1079   0.9274   0.0618
  -9.500  -0.2830   0.07549   0.06862  -0.1093   0.9199   0.0609
  -9.250  -0.3102   0.07136   0.06438  -0.1093   0.9132   0.0600
  -9.000  -0.3404   0.06910   0.06202  -0.1054   0.9053   0.0596
  -8.750  -0.3610   0.06619   0.05891  -0.1027   0.8990   0.0593
  -8.500  -0.3778   0.06375   0.05626  -0.0993   0.8935   0.0592
  -8.250  -0.3950   0.06187   0.05419  -0.0948   0.8871   0.0592
  -8.000  -0.3980   0.05921   0.05124  -0.0925   0.8828   0.0595
  -7.750  -0.4053   0.05728   0.04907  -0.0888   0.8778   0.0598
  -7.500  -0.4126   0.05571   0.04729  -0.0846   0.8725   0.0604
  -7.250  -0.4071   0.05376   0.04505  -0.0824   0.8687   0.0621
  -7.000  -0.3952   0.05144   0.04231  -0.0813   0.8658   0.0645
  -6.750  -0.4079   0.05052   0.04116  -0.0753   0.8595   0.0657
  -6.500  -0.4013   0.04859   0.03876  -0.0725   0.8555   0.0674
  -6.250  -0.3841   0.04637   0.03593  -0.0712   0.8526   0.0690
  -6.000  -0.3589   0.04474   0.03422  -0.0716   0.8504   0.0723
  -5.750  -0.3633   0.04432   0.03370  -0.0667   0.8446   0.0744
  -5.500  -0.3472   0.04325   0.03234  -0.0651   0.8409   0.0784
  -5.250  -0.3218   0.04189   0.03048  -0.0647   0.8381   0.0824
  -5.000  -0.2930   0.04086   0.02950  -0.0654   0.8359   0.0885
  -4.750  -0.2821   0.04038   0.02882  -0.0627   0.8315   0.0939
  -4.500  -0.2650   0.03974   0.02810  -0.0610   0.8275   0.0992
  -4.250  -0.2398   0.03924   0.02746  -0.0607   0.8243   0.1091
  -4.000  -0.2088   0.03862   0.02681  -0.0614   0.8217   0.1208
  -3.750  -0.1763   0.03805   0.02618  -0.0623   0.8196   0.1389
  -3.500  -0.1770   0.03805   0.02620  -0.0579   0.8137   0.1489
  -3.250  -0.1591   0.03769   0.02589  -0.0566   0.8097   0.1736
  -3.000  -0.1366   0.03704   0.02552  -0.0562   0.8066   0.2159
  -2.750  -0.1165   0.03608   0.02518  -0.0553   0.8040   0.3119
  -2.500  -0.1262   0.03568   0.02537  -0.0495   0.7975   0.4107
  -2.250  -0.0879   0.03665   0.02782  -0.0463   0.7950   0.8314
  -1.750   0.2752   0.03777   0.02735  -0.1001   0.8042   0.9982
  -1.500   0.2567   0.03861   0.02814  -0.0936   0.7953   1.0000
  -1.250   0.2748   0.03883   0.02819  -0.0926   0.7911   1.0000
  -1.000   0.2812   0.03926   0.02851  -0.0897   0.7857   1.0000
  -0.750   0.2763   0.03982   0.02898  -0.0850   0.7782   1.0000
  -0.500   0.2991   0.04002   0.02903  -0.0847   0.7744   1.0000
  -0.250   0.2899   0.04066   0.02961  -0.0793   0.7663   1.0000
   0.000   0.3039   0.04098   0.02983  -0.0776   0.7609   1.0000
   0.250   0.3322   0.04113   0.02984  -0.0780   0.7575   1.0000
   0.500   0.3155   0.04187   0.03055  -0.0715   0.7477   1.0000
   0.750   0.3386   0.04209   0.03066  -0.0711   0.7434   1.0000
   1.000   0.3334   0.04270   0.03122  -0.0664   0.7350   1.0000
   1.250   0.3500   0.04300   0.03144  -0.0650   0.7294   1.0000
   1.750   0.3643   0.04389   0.03222  -0.0593   0.7155   1.0000
   2.000   0.3916   0.04402   0.03227  -0.0593   0.7116   1.0000
   2.250   0.3816   0.04473   0.03296  -0.0541   0.7015   1.0000
   2.500   0.4060   0.04488   0.03306  -0.0536   0.6971   1.0000
   2.750   0.4003   0.04555   0.03371  -0.0492   0.6874   1.0000
   3.000   0.4221   0.04574   0.03386  -0.0483   0.6825   1.0000
   3.250   0.4199   0.04636   0.03447  -0.0443   0.6731   1.0000
   3.500   0.4405   0.04655   0.03463  -0.0433   0.6677   1.0000
   3.750   0.4401   0.04719   0.03525  -0.0397   0.6585   1.0000
   4.000   0.4603   0.04737   0.03542  -0.0386   0.6529   1.0000
   4.250   0.4611   0.04804   0.03609  -0.0353   0.6437   1.0000
   4.500   0.4821   0.04820   0.03624  -0.0343   0.6380   1.0000
   4.750   0.4840   0.04896   0.03700  -0.0313   0.6285   1.0000
   5.000   0.5067   0.04912   0.03718  -0.0306   0.6231   1.0000
   5.250   0.5102   0.04996   0.03803  -0.0280   0.6132   1.0000
   5.500   0.5350   0.05010   0.03818  -0.0276   0.6080   1.0000
   5.750   0.5395   0.05105   0.03916  -0.0254   0.5977   1.0000
   6.000   0.5665   0.05110   0.03924  -0.0252   0.5927   1.0000
   6.250   0.5711   0.05220   0.04039  -0.0232   0.5820   1.0000
   6.500   0.6002   0.05215   0.04040  -0.0232   0.5774   1.0000
   7.000   0.6359   0.05316   0.04154  -0.0215   0.5620   1.0000
   7.250   0.6396   0.05455   0.04299  -0.0198   0.5503   1.0000
   7.750   0.6759   0.05570   0.04429  -0.0184   0.5344   1.0000
   8.000   0.6858   0.05687   0.04554  -0.0173   0.5242   1.0000
   8.250   0.7133   0.05676   0.04556  -0.0170   0.5183   1.0000
   8.500   0.7205   0.05820   0.04708  -0.0159   0.5072   1.0000
   8.750   0.7517   0.05772   0.04673  -0.0157   0.5023   1.0000
   9.000   0.7572   0.05934   0.04846  -0.0146   0.4903   1.0000
   9.250   0.7915   0.05847   0.04774  -0.0144   0.4862   1.0000
   9.500   0.7953   0.06030   0.04967  -0.0133   0.4736   1.0000
  10.000   0.8352   0.06095   0.05062  -0.0119   0.4571   1.0000
  10.250   0.8406   0.06275   0.05254  -0.0110   0.4448   1.0000
  10.500   0.8776   0.06117   0.05115  -0.0105   0.4406   1.0000
  10.750   0.8811   0.06315   0.05325  -0.0095   0.4276   1.0000
  11.250   0.9268   0.06286   0.05333  -0.0079   0.4105   1.0000
  11.750   0.9400   0.06619   0.05694  -0.0062   0.3851   1.0000
  12.000   0.9856   0.06315   0.05415  -0.0053   0.3790   1.0000
  12.500   0.9979   0.06640   0.05769  -0.0035   0.3519   1.0000
  12.750   1.0096   0.06731   0.05876  -0.0025   0.3384   1.0000
  13.000   1.0240   0.06782   0.05942  -0.0016   0.3246   1.0000
  13.250   1.0381   0.06826   0.06001  -0.0006   0.3092   1.0000
  13.500   1.0499   0.06893   0.06079   0.0004   0.2926   1.0000
  13.750   1.0627   0.06939   0.06130   0.0014   0.2743   1.0000
  14.000   1.0675   0.07102   0.06295   0.0022   0.2557   1.0000
  14.250   1.0647   0.07384   0.06584   0.0025   0.2368   1.0000
  14.500   1.0648   0.07629   0.06829   0.0029   0.2171   1.0000
  14.750   1.0650   0.07878   0.07073   0.0032   0.1975   1.0000
  15.000   1.0592   0.08243   0.07441   0.0029   0.1787   1.0000
  15.250   1.0542   0.08601   0.07795   0.0026   0.1603   1.0000
  15.500   1.0491   0.08969   0.08155   0.0021   0.1435   1.0000
  15.750   1.0434   0.09360   0.08535   0.0014   0.1283   1.0000
  16.000   1.0378   0.09768   0.08936   0.0005   0.1149   1.0000
  16.250   1.0323   0.10188   0.09354  -0.0005   0.1028   1.0000
  16.500   1.0280   0.10604   0.09771  -0.0016   0.0924   1.0000
  16.750   1.0249   0.11006   0.10174  -0.0028   0.0836   1.0000
  17.000   1.0234   0.11369   0.10525  -0.0039   0.0767   1.0000
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