Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

AH 93-157 (ah93157-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: AH 93-157 (ah93157-il)
Reynolds number: 50,000
Max Cl/Cd: 14.44 at α=12.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ah93157-il-50000-n5.txt
Download as CSV file: xf-ah93157-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.3073   0.11380   0.10715  -0.0722   0.9698   0.0611
 -11.000  -0.3038   0.10917   0.10252  -0.0754   0.9643   0.0610
 -10.750  -0.2993   0.10418   0.09752  -0.0793   0.9599   0.0609
 -10.500  -0.2983   0.09836   0.09170  -0.0845   0.9559   0.0610
 -10.250  -0.3006   0.09333   0.08668  -0.0880   0.9497   0.0608
 -10.000  -0.3030   0.08711   0.08043  -0.0935   0.9448   0.0606
  -9.750  -0.3105   0.08148   0.07475  -0.0981   0.9394   0.0602
  -9.500  -0.3252   0.07726   0.07047  -0.0998   0.9320   0.0599
  -9.250  -0.3387   0.07281   0.06589  -0.1017   0.9264   0.0596
  -9.000  -0.3623   0.07072   0.06373  -0.0983   0.9172   0.0593
  -8.750  -0.3730   0.06699   0.05978  -0.0979   0.9115   0.0591
  -8.500  -0.3929   0.06488   0.05752  -0.0937   0.9033   0.0591
  -8.250  -0.4014   0.06179   0.05414  -0.0917   0.8977   0.0591
  -8.000  -0.4110   0.05917   0.05121  -0.0884   0.8917   0.0594
  -7.750  -0.4202   0.05694   0.04868  -0.0845   0.8850   0.0598
  -7.500  -0.4187   0.05383   0.04497  -0.0825   0.8806   0.0611
  -7.250  -0.4196   0.05228   0.04329  -0.0790   0.8748   0.0625
  -7.000  -0.4131   0.05090   0.04179  -0.0766   0.8695   0.0640
  -6.750  -0.3977   0.04890   0.03947  -0.0757   0.8658   0.0660
  -6.500  -0.3801   0.04671   0.03685  -0.0748   0.8625   0.0677
  -6.250  -0.3826   0.04570   0.03559  -0.0702   0.8558   0.0693
  -6.000  -0.3650   0.04399   0.03331  -0.0688   0.8517   0.0728
  -5.750  -0.3386   0.04244   0.03164  -0.0692   0.8489   0.0766
  -5.500  -0.3251   0.04151   0.03053  -0.0671   0.8442   0.0793
  -5.250  -0.3115   0.04071   0.02946  -0.0649   0.8390   0.0838
  -5.000  -0.2850   0.03963   0.02822  -0.0649   0.8356   0.0895
  -4.750  -0.2520   0.03869   0.02711  -0.0659   0.8330   0.0973
  -4.500  -0.2351   0.03818   0.02653  -0.0642   0.8284   0.1044
  -4.250  -0.2183   0.03782   0.02605  -0.0625   0.8232   0.1130
  -4.000  -0.1892   0.03724   0.02544  -0.0628   0.8197   0.1261
  -3.750  -0.1567   0.03661   0.02475  -0.0637   0.8170   0.1454
  -3.500  -0.1482   0.03644   0.02461  -0.0608   0.8114   0.1617
  -3.250  -0.1351   0.03607   0.02442  -0.0587   0.8061   0.1877
  -3.000  -0.1134   0.03533   0.02402  -0.0581   0.8025   0.2442
  -2.750  -0.0960   0.03412   0.02366  -0.0567   0.7997   0.3801
  -2.500  -0.0505   0.03501   0.02622  -0.0549   0.7967   0.8036
  -2.250  -0.0646   0.03557   0.02664  -0.0474   0.7893   0.8541
  -2.000   0.1979   0.03641   0.02635  -0.0866   0.8002   0.9704
  -1.750   0.3087   0.03569   0.02520  -0.1032   0.8002   0.9973
  -1.500   0.3039   0.03648   0.02593  -0.0990   0.7913   1.0000
  -1.250   0.3224   0.03665   0.02594  -0.0981   0.7865   1.0000
  -1.000   0.3281   0.03715   0.02632  -0.0951   0.7803   1.0000
  -0.750   0.3282   0.03771   0.02680  -0.0912   0.7727   1.0000
  -0.500   0.3536   0.03781   0.02676  -0.0912   0.7690   1.0000
  -0.250   0.3350   0.03873   0.02764  -0.0843   0.7592   1.0000
   0.000   0.3554   0.03893   0.02773  -0.0835   0.7544   1.0000
   0.500   0.3604   0.04002   0.02868  -0.0763   0.7401   1.0000
   0.750   0.3884   0.04011   0.02866  -0.0766   0.7366   1.0000
   1.000   0.3702   0.04104   0.02957  -0.0700   0.7261   1.0000
   1.250   0.3945   0.04119   0.02963  -0.0696   0.7219   1.0000
   1.500   0.3848   0.04198   0.03039  -0.0643   0.7124   1.0000
   1.750   0.4042   0.04221   0.03055  -0.0632   0.7073   1.0000
   2.000   0.4036   0.04285   0.03116  -0.0593   0.6992   1.0000
   2.250   0.4164   0.04320   0.03145  -0.0572   0.6927   1.0000
   2.500   0.4455   0.04322   0.03142  -0.0573   0.6893   1.0000
   2.750   0.4306   0.04416   0.03235  -0.0516   0.6783   1.0000
   3.000   0.4583   0.04417   0.03232  -0.0515   0.6745   1.0000
   3.250   0.4463   0.04510   0.03324  -0.0463   0.6637   1.0000
   3.500   0.4728   0.04511   0.03321  -0.0459   0.6596   1.0000
   3.750   0.4636   0.04603   0.03412  -0.0412   0.6490   1.0000
   4.000   0.4890   0.04604   0.03412  -0.0407   0.6447   1.0000
   4.250   0.4824   0.04696   0.03504  -0.0365   0.6341   1.0000
   4.500   0.5072   0.04699   0.03506  -0.0358   0.6297   1.0000
   4.750   0.5035   0.04792   0.03600  -0.0321   0.6191   1.0000
   5.000   0.5290   0.04794   0.03603  -0.0316   0.6146   1.0000
   5.250   0.5278   0.04898   0.03707  -0.0285   0.6040   1.0000
   5.500   0.5545   0.04897   0.03709  -0.0282   0.5994   1.0000
   5.750   0.5553   0.05012   0.03825  -0.0256   0.5886   1.0000
   6.000   0.5837   0.05006   0.03824  -0.0254   0.5841   1.0000
   6.250   0.5852   0.05136   0.03958  -0.0232   0.5731   1.0000
   6.500   0.6152   0.05120   0.03947  -0.0231   0.5687   1.0000
   6.750   0.6172   0.05262   0.04092  -0.0212   0.5573   1.0000
   7.000   0.6481   0.05239   0.04078  -0.0212   0.5531   1.0000
   7.250   0.6502   0.05393   0.04238  -0.0194   0.5414   1.0000
   7.500   0.6823   0.05359   0.04212  -0.0194   0.5375   1.0000
   7.750   0.6843   0.05525   0.04383  -0.0178   0.5254   1.0000
   8.250   0.7187   0.05659   0.04537  -0.0163   0.5092   1.0000
   8.750   0.7535   0.05793   0.04690  -0.0149   0.4930   1.0000
   9.000   0.7584   0.05968   0.04876  -0.0138   0.4815   1.0000
   9.250   0.7889   0.05920   0.04842  -0.0135   0.4769   1.0000
   9.750   0.8250   0.06031   0.04978  -0.0121   0.4607   1.0000
  10.000   0.8256   0.06263   0.05222  -0.0111   0.4480   1.0000
  10.500   0.8609   0.06378   0.05365  -0.0097   0.4313   1.0000
  11.000   0.8981   0.06465   0.05483  -0.0083   0.4148   1.0000
  11.250   0.8971   0.06732   0.05762  -0.0075   0.4018   1.0000
  11.750   0.9361   0.06779   0.05842  -0.0060   0.3847   1.0000
  12.000   0.9362   0.07038   0.06116  -0.0054   0.3720   1.0000
  12.250   0.9778   0.06772   0.05872  -0.0043   0.3665   1.0000
  12.500   0.9815   0.06974   0.06089  -0.0035   0.3538   1.0000
  12.750   0.9822   0.07220   0.06348  -0.0030   0.3408   1.0000
  13.000   0.9916   0.07347   0.06491  -0.0022   0.3285   1.0000
  13.250   1.0156   0.07255   0.06418  -0.0011   0.3165   1.0000
  13.500   1.0317   0.07251   0.06427   0.0000   0.3015   1.0000
  13.750   1.0399   0.07352   0.06538   0.0009   0.2846   1.0000
  14.000   1.0464   0.07481   0.06676   0.0016   0.2666   1.0000
  14.250   1.0565   0.07552   0.06750   0.0025   0.2469   1.0000
  14.500   1.0561   0.07807   0.07009   0.0027   0.2282   1.0000
  14.750   1.0526   0.08125   0.07332   0.0026   0.2090   1.0000
  15.000   1.0525   0.08386   0.07588   0.0026   0.1885   1.0000
  15.250   1.0484   0.08729   0.07927   0.0023   0.1690   1.0000
  15.500   1.0432   0.09102   0.08295   0.0017   0.1502   1.0000
  15.750   1.0381   0.09482   0.08662   0.0011   0.1334   1.0000
  16.000   1.0329   0.09876   0.09046   0.0003   0.1191   1.0000
  16.250   1.0282   0.10278   0.09442  -0.0007   0.1070   1.0000
  16.500   1.0248   0.10672   0.09833  -0.0017   0.0967   1.0000
  16.750   1.0227   0.11048   0.10206  -0.0027   0.0883   1.0000
  17.000   1.0219   0.11408   0.10563  -0.0038   0.0811   1.0000
<< Back to AH 93-157 (ah93157-il)

Polar data table (+)

Polar graphs


<< Back to AH 93-157 (ah93157-il)