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

AH 93-156 (ah93156-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: AH 93-156 (ah93156-il)
Reynolds number: 500,000
Max Cl/Cd: 94.14 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ah93156-il-500000-n5.txt
Download as CSV file: xf-ah93156-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.750  -0.6025   0.05672   0.05296  -0.1129   0.8034   0.0110
 -14.500  -0.6478   0.04576   0.04169  -0.1209   0.8000   0.0109
 -14.250  -0.6614   0.04171   0.03748  -0.1225   0.7964   0.0110
 -14.000  -0.6768   0.03823   0.03382  -0.1225   0.7928   0.0110
 -13.750  -0.6866   0.03565   0.03106  -0.1214   0.7895   0.0111
 -13.500  -0.6865   0.03403   0.02931  -0.1202   0.7866   0.0113
 -13.250  -0.6888   0.03227   0.02742  -0.1184   0.7836   0.0114
 -13.000  -0.6905   0.03061   0.02561  -0.1163   0.7807   0.0115
 -12.750  -0.6894   0.02919   0.02403  -0.1141   0.7779   0.0117
 -12.500  -0.6855   0.02798   0.02266  -0.1119   0.7754   0.0119
 -12.250  -0.6819   0.02673   0.02124  -0.1094   0.7729   0.0120
 -12.000  -0.6755   0.02563   0.02000  -0.1071   0.7704   0.0123
 -11.750  -0.6676   0.02463   0.01887  -0.1048   0.7677   0.0125
 -11.500  -0.6590   0.02367   0.01777  -0.1025   0.7651   0.0127
 -11.250  -0.6483   0.02287   0.01681  -0.1002   0.7628   0.0129
 -11.000  -0.6385   0.02204   0.01584  -0.0978   0.7606   0.0131
 -10.750  -0.6264   0.02129   0.01500  -0.0957   0.7587   0.0134
 -10.500  -0.6105   0.02064   0.01426  -0.0942   0.7569   0.0137
 -10.250  -0.5930   0.02002   0.01357  -0.0929   0.7548   0.0140
 -10.000  -0.5736   0.01953   0.01302  -0.0919   0.7526   0.0145
  -9.750  -0.5538   0.01902   0.01243  -0.0909   0.7504   0.0149
  -9.500  -0.5335   0.01850   0.01181  -0.0899   0.7484   0.0154
  -9.250  -0.5125   0.01799   0.01121  -0.0891   0.7466   0.0160
  -9.000  -0.4909   0.01752   0.01062  -0.0882   0.7449   0.0164
  -8.750  -0.4710   0.01690   0.00994  -0.0872   0.7432   0.0170
  -8.500  -0.4491   0.01646   0.00944  -0.0865   0.7415   0.0175
  -8.250  -0.4263   0.01607   0.00901  -0.0859   0.7397   0.0182
  -8.000  -0.4034   0.01567   0.00857  -0.0853   0.7376   0.0189
  -7.750  -0.3801   0.01529   0.00813  -0.0847   0.7357   0.0197
  -7.500  -0.3563   0.01495   0.00772  -0.0842   0.7340   0.0204
  -7.250  -0.3334   0.01452   0.00728  -0.0835   0.7323   0.0216
  -7.000  -0.3091   0.01423   0.00695  -0.0831   0.7305   0.0228
  -6.750  -0.2847   0.01395   0.00662  -0.0827   0.7288   0.0240
  -6.500  -0.2601   0.01367   0.00627  -0.0823   0.7271   0.0251
  -6.250  -0.2360   0.01334   0.00591  -0.0818   0.7255   0.0265
  -6.000  -0.2112   0.01307   0.00565  -0.0815   0.7238   0.0283
  -5.750  -0.1860   0.01285   0.00541  -0.0812   0.7221   0.0303
  -5.500  -0.1611   0.01259   0.00513  -0.0808   0.7201   0.0324
  -5.250  -0.1360   0.01235   0.00489  -0.0805   0.7182   0.0350
  -5.000  -0.1103   0.01216   0.00467  -0.0803   0.7163   0.0378
  -4.750  -0.0850   0.01193   0.00445  -0.0800   0.7147   0.0418
  -4.500  -0.0591   0.01176   0.00425  -0.0798   0.7131   0.0459
  -4.250  -0.0333   0.01157   0.00405  -0.0796   0.7115   0.0514
  -4.000  -0.0074   0.01141   0.00390  -0.0794   0.7097   0.0578
  -3.750   0.0182   0.01122   0.00376  -0.0792   0.7078   0.0668
  -3.500   0.0439   0.01104   0.00363  -0.0790   0.7058   0.0777
  -3.250   0.0696   0.01086   0.00350  -0.0788   0.7037   0.0934
  -3.000   0.0953   0.01068   0.00338  -0.0786   0.7017   0.1127
  -2.750   0.1207   0.01047   0.00326  -0.0783   0.6999   0.1403
  -2.500   0.1461   0.01025   0.00314  -0.0781   0.6980   0.1750
  -2.250   0.1708   0.00997   0.00303  -0.0778   0.6962   0.2265
  -2.000   0.1943   0.00965   0.00295  -0.0773   0.6941   0.2949
  -1.750   0.2168   0.00927   0.00288  -0.0767   0.6915   0.3808
  -1.500   0.2379   0.00880   0.00278  -0.0758   0.6890   0.4845
  -1.250   0.2540   0.00807   0.00265  -0.0738   0.6865   0.6505
  -1.000   0.2733   0.00792   0.00299  -0.0716   0.6840   0.7795
  -0.750   0.2998   0.00808   0.00314  -0.0711   0.6813   0.8132
  -0.500   0.3265   0.00821   0.00326  -0.0708   0.6781   0.8298
  -0.250   0.3532   0.00835   0.00338  -0.0705   0.6748   0.8421
   0.000   0.3793   0.00855   0.00358  -0.0700   0.6718   0.8513
   0.250   0.4053   0.00874   0.00374  -0.0694   0.6688   0.8612
   0.500   0.4308   0.00897   0.00394  -0.0687   0.6662   0.8694
   0.750   0.4559   0.00912   0.00409  -0.0680   0.6631   0.8762
   1.000   0.4812   0.00922   0.00421  -0.0674   0.6595   0.8801
   1.250   0.5080   0.00923   0.00421  -0.0673   0.6560   0.8824
   1.500   0.5356   0.00923   0.00416  -0.0674   0.6526   0.8841
   1.750   0.5631   0.00924   0.00414  -0.0676   0.6493   0.8859
   2.000   0.5904   0.00924   0.00416  -0.0678   0.6452   0.8874
   2.250   0.6178   0.00925   0.00415  -0.0680   0.6410   0.8889
   2.500   0.6444   0.00925   0.00413  -0.0679   0.6370   0.8898
   2.750   0.6708   0.00926   0.00415  -0.0678   0.6326   0.8907
   3.000   0.6969   0.00927   0.00418  -0.0677   0.6274   0.8918
   3.250   0.7230   0.00929   0.00418  -0.0675   0.6223   0.8929
   3.500   0.7488   0.00932   0.00423  -0.0673   0.6163   0.8941
   3.750   0.7743   0.00935   0.00426  -0.0671   0.6093   0.8951
   4.000   0.7996   0.00939   0.00430  -0.0669   0.6024   0.8964
   4.250   0.8245   0.00945   0.00435  -0.0665   0.5946   0.8978
   4.500   0.8491   0.00951   0.00441  -0.0662   0.5861   0.8991
   4.750   0.8726   0.00960   0.00447  -0.0656   0.5760   0.9002
   5.000   0.8957   0.00970   0.00456  -0.0650   0.5643   0.9014
   5.250   0.9179   0.00984   0.00466  -0.0642   0.5519   0.9026
   5.500   0.9376   0.00998   0.00478  -0.0629   0.5386   0.9038
   5.750   0.9555   0.01015   0.00492  -0.0612   0.5244   0.9050
   6.000   0.9715   0.01035   0.00509  -0.0592   0.5097   0.9061
   6.250   0.9843   0.01057   0.00527  -0.0566   0.4952   0.9076
   6.500   0.9940   0.01082   0.00549  -0.0534   0.4809   0.9093
   6.750   1.0029   0.01117   0.00580  -0.0501   0.4660   0.9115
   7.000   1.0124   0.01156   0.00616  -0.0472   0.4522   0.9132
   7.250   1.0207   0.01204   0.00660  -0.0442   0.4376   0.9149
   7.500   1.0290   0.01258   0.00710  -0.0413   0.4235   0.9165
   8.000   1.0463   0.01368   0.00817  -0.0360   0.3968   0.9199
   8.250   1.0549   0.01432   0.00879  -0.0335   0.3827   0.9215
   8.500   1.0648   0.01496   0.00942  -0.0313   0.3700   0.9230
   8.750   1.0717   0.01576   0.01017  -0.0287   0.3534   0.9247
   9.000   1.0779   0.01664   0.01100  -0.0262   0.3357   0.9263
   9.250   1.0817   0.01767   0.01195  -0.0235   0.3145   0.9280
   9.500   1.0869   0.01869   0.01290  -0.0211   0.2932   0.9297
   9.750   1.0901   0.01984   0.01394  -0.0185   0.2707   0.9316
  10.000   1.0935   0.02104   0.01504  -0.0161   0.2467   0.9332
  10.250   1.0982   0.02223   0.01615  -0.0140   0.2259   0.9348
  10.500   1.1022   0.02351   0.01733  -0.0119   0.2019   0.9365
  11.000   1.1145   0.02601   0.01968  -0.0085   0.1629   0.9396
  11.250   1.1179   0.02753   0.02107  -0.0067   0.1394   0.9413
  11.500   1.1249   0.02892   0.02239  -0.0055   0.1212   0.9428
  12.000   1.1354   0.03221   0.02550  -0.0032   0.0814   0.9460
  12.250   1.1415   0.03400   0.02719  -0.0024   0.0640   0.9480
  12.500   1.1461   0.03602   0.02911  -0.0018   0.0463   0.9501
  12.750   1.1567   0.03765   0.03074  -0.0017   0.0382   0.9521
  13.000   1.1676   0.03932   0.03242  -0.0017   0.0319   0.9541
  13.250   1.1780   0.04109   0.03420  -0.0018   0.0262   0.9561
  13.500   1.1893   0.04289   0.03605  -0.0021   0.0223   0.9583
  13.750   1.2006   0.04485   0.03804  -0.0027   0.0187   0.9610
  14.000   1.2126   0.04682   0.04006  -0.0034   0.0159   0.9637
  14.250   1.2240   0.04883   0.04213  -0.0041   0.0142   0.9667
  14.500   1.2330   0.05085   0.04420  -0.0044   0.0127   0.9754
  14.750   1.2421   0.05311   0.04653  -0.0051   0.0114   0.9937
  15.000   1.2418   0.05492   0.04840  -0.0031   0.0107   1.0000
  15.250   1.2463   0.05719   0.05074  -0.0029   0.0098   1.0000
  15.500   1.2500   0.05958   0.05318  -0.0027   0.0092   1.0000
  15.750   1.2542   0.06198   0.05566  -0.0026   0.0087   1.0000
  16.000   1.2586   0.06439   0.05814  -0.0027   0.0081   1.0000
  16.250   1.2612   0.06705   0.06088  -0.0028   0.0077   1.0000
  16.500   1.2627   0.06990   0.06379  -0.0029   0.0072   1.0000
  16.750   1.2615   0.07312   0.06710  -0.0032   0.0069   1.0000
  17.000   1.2627   0.07611   0.07019  -0.0036   0.0068   1.0000
  17.250   1.2649   0.07902   0.07319  -0.0041   0.0066   1.0000
  17.500   1.2646   0.08231   0.07657  -0.0046   0.0061   1.0000
  17.750   1.2641   0.08569   0.08005  -0.0053   0.0062   1.0000
  18.000   1.2620   0.08930   0.08376  -0.0062   0.0059   1.0000
  18.250   1.2602   0.09295   0.08751  -0.0071   0.0057   1.0000
  18.500   1.2581   0.09671   0.09136  -0.0082   0.0057   1.0000
  18.750   1.2554   0.10059   0.09533  -0.0094   0.0055   1.0000
  19.000   1.2518   0.10468   0.09952  -0.0107   0.0054   1.0000
  19.250   1.2467   0.10901   0.10395  -0.0122   0.0053   1.0000
<< Back to AH 93-156 (ah93156-il)

Polar data table (+)

Polar graphs


<< Back to AH 93-156 (ah93156-il)