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AH 88-K-136/16 (ah88k136-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: AH 88-K-136/16 (ah88k136-il)
Reynolds number: 500,000
Max Cl/Cd: 87.07 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ah88k136-il-500000-n5.txt
Download as CSV file: xf-ah88k136-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AH 88-K-136/16                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.6525   0.04444   0.04093  -0.0995   0.7843   0.0075
 -12.500  -0.6586   0.04229   0.03871  -0.0980   0.7833   0.0077
 -12.250  -0.6991   0.03742   0.03351  -0.0932   0.7814   0.0076
 -12.000  -0.6968   0.03621   0.03222  -0.0908   0.7800   0.0077
 -11.750  -0.6987   0.03469   0.03058  -0.0877   0.7786   0.0080
 -11.500  -0.7047   0.03282   0.02850  -0.0837   0.7773   0.0081
 -11.250  -0.7102   0.03097   0.02643  -0.0794   0.7762   0.0082
 -11.000  -0.7119   0.02946   0.02471  -0.0752   0.7752   0.0083
 -10.750  -0.7083   0.02816   0.02320  -0.0718   0.7743   0.0085
 -10.500  -0.7022   0.02663   0.02140  -0.0688   0.7735   0.0088
 -10.250  -0.6919   0.02532   0.01986  -0.0663   0.7729   0.0090
 -10.000  -0.6798   0.02407   0.01839  -0.0640   0.7722   0.0092
  -9.750  -0.6642   0.02309   0.01721  -0.0622   0.7716   0.0094
  -9.500  -0.6493   0.02197   0.01591  -0.0603   0.7710   0.0096
  -9.250  -0.6313   0.02129   0.01515  -0.0590   0.7705   0.0101
  -9.000  -0.6126   0.02060   0.01437  -0.0577   0.7690   0.0103
  -8.750  -0.5928   0.01998   0.01365  -0.0565   0.7675   0.0106
  -8.500  -0.5721   0.01940   0.01298  -0.0555   0.7662   0.0111
  -8.250  -0.5508   0.01883   0.01231  -0.0545   0.7650   0.0116
  -8.000  -0.5292   0.01826   0.01162  -0.0536   0.7639   0.0120
  -7.750  -0.5068   0.01774   0.01100  -0.0528   0.7628   0.0125
  -7.500  -0.4851   0.01714   0.01035  -0.0519   0.7618   0.0133
  -7.250  -0.4618   0.01675   0.00991  -0.0513   0.7609   0.0140
  -7.000  -0.4381   0.01641   0.00951  -0.0507   0.7602   0.0150
  -6.750  -0.4146   0.01599   0.00901  -0.0500   0.7595   0.0158
  -6.500  -0.3917   0.01550   0.00847  -0.0493   0.7589   0.0168
  -6.250  -0.3679   0.01511   0.00804  -0.0487   0.7583   0.0178
  -6.000  -0.3436   0.01480   0.00768  -0.0482   0.7577   0.0192
  -5.750  -0.3191   0.01449   0.00730  -0.0476   0.7571   0.0205
  -5.500  -0.2955   0.01408   0.00687  -0.0470   0.7565   0.0222
  -5.250  -0.2722   0.01391   0.00671  -0.0463   0.7545   0.0240
  -5.000  -0.2483   0.01375   0.00652  -0.0457   0.7526   0.0258
  -4.750  -0.2245   0.01348   0.00627  -0.0451   0.7510   0.0287
  -4.500  -0.2000   0.01328   0.00605  -0.0446   0.7497   0.0318
  -4.250  -0.1756   0.01304   0.00581  -0.0441   0.7485   0.0355
  -4.000  -0.1508   0.01284   0.00560  -0.0436   0.7476   0.0398
  -3.750  -0.1261   0.01261   0.00539  -0.0432   0.7466   0.0454
  -3.500  -0.1008   0.01241   0.00517  -0.0428   0.7457   0.0511
  -3.250  -0.0758   0.01218   0.00496  -0.0423   0.7449   0.0591
  -3.000  -0.0505   0.01197   0.00477  -0.0419   0.7442   0.0685
  -2.750  -0.0252   0.01175   0.00457  -0.0416   0.7435   0.0810
  -2.500   0.0001   0.01154   0.00439  -0.0412   0.7428   0.0963
  -2.250   0.0239   0.01142   0.00436  -0.0406   0.7409   0.1170
  -2.000   0.0469   0.01131   0.00438  -0.0399   0.7382   0.1456
  -1.750   0.0703   0.01109   0.00430  -0.0393   0.7361   0.1866
  -1.500   0.0921   0.01070   0.00416  -0.0383   0.7344   0.2595
  -1.250   0.1076   0.00997   0.00397  -0.0361   0.7328   0.4178
  -1.000   0.1159   0.00915   0.00375  -0.0322   0.7313   0.5892
  -0.750   0.1673   0.00852   0.00416  -0.0368   0.7305   0.8676
  -0.500   0.1839   0.00863   0.00423  -0.0340   0.7293   0.8947
  -0.250   0.2086   0.00877   0.00433  -0.0331   0.7279   0.9088
   0.000   0.2453   0.00917   0.00474  -0.0349   0.7241   0.9179
   0.250   0.2614   0.00929   0.00485  -0.0322   0.7209   0.9282
   0.500   0.3357   0.00965   0.00517  -0.0420   0.7193   0.9312
   0.750   0.3782   0.00970   0.00518  -0.0452   0.7174   0.9334
   1.000   0.4095   0.00961   0.00506  -0.0461   0.7154   0.9351
   1.250   0.4384   0.00954   0.00497  -0.0464   0.7132   0.9372
   1.500   0.4460   0.00962   0.00508  -0.0422   0.7084   0.9435
   1.750   0.4787   0.00957   0.00503  -0.0435   0.7048   0.9441
   2.000   0.5109   0.00947   0.00491  -0.0446   0.7018   0.9448
   2.250   0.5424   0.00938   0.00480  -0.0456   0.6988   0.9455
   2.500   0.5714   0.00942   0.00489  -0.0462   0.6929   0.9464
   2.750   0.6012   0.00936   0.00483  -0.0468   0.6884   0.9473
   3.000   0.6304   0.00929   0.00475  -0.0472   0.6836   0.9483
   3.250   0.6573   0.00930   0.00480  -0.0473   0.6765   0.9495
   3.500   0.6845   0.00921   0.00469  -0.0474   0.6703   0.9507
   3.750   0.7093   0.00923   0.00474  -0.0470   0.6606   0.9525
   4.000   0.7307   0.00921   0.00472  -0.0458   0.6513   0.9544
   4.250   0.7405   0.00919   0.00468  -0.0420   0.6396   0.9581
   4.500   0.7684   0.00921   0.00467  -0.0423   0.6236   0.9587
   4.750   0.7949   0.00929   0.00470  -0.0423   0.6050   0.9593
   5.000   0.8195   0.00943   0.00479  -0.0420   0.5829   0.9602
   5.250   0.8420   0.00967   0.00494  -0.0413   0.5576   0.9613
   5.500   0.8624   0.01002   0.00519  -0.0403   0.5283   0.9628
   5.750   0.8768   0.01053   0.00555  -0.0381   0.4920   0.9651
   6.000   0.8787   0.01121   0.00603  -0.0337   0.4477   0.9688
   6.250   0.8802   0.01197   0.00659  -0.0294   0.4068   0.9723
   6.500   0.8904   0.01306   0.00742  -0.0276   0.3523   0.9746
   6.750   0.8923   0.01396   0.00814  -0.0242   0.3144   0.9779
   7.000   0.8881   0.01497   0.00897  -0.0198   0.2754   0.9822
   7.250   0.8964   0.01596   0.00977  -0.0179   0.2371   0.9846
   7.500   0.9067   0.01705   0.01062  -0.0166   0.1903   0.9862
   7.750   0.9155   0.01818   0.01149  -0.0151   0.1422   0.9880
   8.000   0.9240   0.01931   0.01239  -0.0134   0.0999   0.9899
   8.250   0.9319   0.02046   0.01333  -0.0116   0.0615   0.9918
   8.500   0.9414   0.02153   0.01425  -0.0100   0.0363   0.9934
   8.750   0.9568   0.02234   0.01504  -0.0091   0.0277   0.9950
   9.000   0.9733   0.02317   0.01585  -0.0086   0.0218   0.9967
   9.250   0.9910   0.02389   0.01660  -0.0081   0.0188   0.9979
   9.500   1.0074   0.02475   0.01747  -0.0076   0.0166   0.9990
   9.750   1.0252   0.02554   0.01833  -0.0073   0.0153   0.9998
  10.000   1.0342   0.02627   0.01911  -0.0052   0.0145   1.0000
  10.250   1.0390   0.02703   0.01990  -0.0023   0.0135   1.0000
  10.500   1.0417   0.02791   0.02081   0.0008   0.0127   1.0000
  10.750   1.0473   0.02866   0.02162   0.0034   0.0121   1.0000
  11.000   1.0537   0.02942   0.02243   0.0058   0.0115   1.0000
  11.250   1.0600   0.03028   0.02334   0.0081   0.0108   1.0000
  11.500   1.0666   0.03127   0.02438   0.0102   0.0104   1.0000
  11.750   1.0731   0.03240   0.02556   0.0121   0.0100   1.0000
  12.000   1.0769   0.03386   0.02707   0.0140   0.0096   1.0000
  12.250   1.0851   0.03506   0.02834   0.0154   0.0093   1.0000
  12.500   1.0921   0.03642   0.02978   0.0168   0.0089   1.0000
  12.750   1.0998   0.03778   0.03121   0.0180   0.0086   1.0000
  13.000   1.1075   0.03919   0.03268   0.0191   0.0082   1.0000
  13.250   1.1154   0.04063   0.03419   0.0201   0.0079   1.0000
  13.500   1.1192   0.04248   0.03613   0.0213   0.0078   1.0000
  13.750   1.1279   0.04392   0.03761   0.0220   0.0073   1.0000
  14.000   1.1294   0.04610   0.03984   0.0230   0.0070   1.0000
  14.250   1.1322   0.04822   0.04207   0.0239   0.0068   1.0000
  14.500   1.1368   0.05021   0.04414   0.0245   0.0069   1.0000
  14.750   1.1432   0.05208   0.04611   0.0250   0.0065   1.0000
  15.000   1.1456   0.05440   0.04854   0.0256   0.0063   1.0000
  15.250   1.1488   0.05671   0.05095   0.0259   0.0062   1.0000
  15.500   1.1485   0.05944   0.05379   0.0263   0.0063   1.0000
  15.750   1.1513   0.06191   0.05636   0.0264   0.0059   1.0000
  16.000   1.1518   0.06469   0.05925   0.0265   0.0058   1.0000
  16.250   1.1533   0.06745   0.06210   0.0264   0.0057   1.0000
  16.500   1.1534   0.07043   0.06518   0.0261   0.0055   1.0000
  16.750   1.1553   0.07329   0.06813   0.0257   0.0054   1.0000
  17.000   1.1510   0.07690   0.07185   0.0253   0.0054   1.0000
  17.250   1.1493   0.08032   0.07539   0.0247   0.0053   1.0000
  17.500   1.1486   0.08372   0.07887   0.0238   0.0052   1.0000
  17.750   1.1437   0.08771   0.08298   0.0229   0.0052   1.0000
  18.000   1.1375   0.09198   0.08734   0.0216   0.0050   1.0000
  18.250   1.1283   0.09673   0.09220   0.0203   0.0049   1.0000
  18.500   1.1252   0.10074   0.09636   0.0190   0.0050   1.0000
  18.750   1.1143   0.10596   0.10171   0.0173   0.0049   1.0000
  19.000   1.1086   0.11056   0.10643   0.0155   0.0049   1.0000
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