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AH 88-K-136/16 (ah88k136-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: AH 88-K-136/16 (ah88k136-il)
Reynolds number: 1,000,000
Max Cl/Cd: 113.65 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ah88k136-il-1000000.txt
Download as CSV file: xf-ah88k136-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.6021   0.04606   0.04345  -0.1046   0.7889   0.0083
 -12.500  -0.6119   0.04335   0.04065  -0.1039   0.7881   0.0085
 -12.250  -0.6803   0.03648   0.03337  -0.0977   0.7869   0.0082
 -12.000  -0.6761   0.03554   0.03237  -0.0954   0.7863   0.0084
 -11.750  -0.6932   0.03310   0.02970  -0.0904   0.7855   0.0085
 -11.500  -0.7069   0.03094   0.02732  -0.0851   0.7847   0.0086
 -11.250  -0.7173   0.02905   0.02522  -0.0797   0.7836   0.0086
 -11.000  -0.7224   0.02752   0.02351  -0.0748   0.7823   0.0086
 -10.750  -0.7191   0.02620   0.02201  -0.0712   0.7808   0.0088
 -10.500  -0.7141   0.02463   0.02023  -0.0678   0.7795   0.0089
 -10.250  -0.7027   0.02354   0.01896  -0.0654   0.7784   0.0091
 -10.000  -0.6902   0.02241   0.01766  -0.0631   0.7774   0.0092
  -9.750  -0.6738   0.02162   0.01672  -0.0614   0.7765   0.0093
  -9.500  -0.6549   0.02106   0.01605  -0.0600   0.7757   0.0094
  -9.250  -0.6472   0.01884   0.01356  -0.0569   0.7749   0.0102
  -9.000  -0.6261   0.01841   0.01308  -0.0560   0.7742   0.0105
  -8.750  -0.6051   0.01786   0.01245  -0.0550   0.7735   0.0108
  -8.500  -0.5836   0.01729   0.01179  -0.0540   0.7729   0.0112
  -8.250  -0.5613   0.01679   0.01120  -0.0531   0.7723   0.0117
  -8.000  -0.5389   0.01629   0.01061  -0.0523   0.7718   0.0121
  -7.750  -0.5150   0.01603   0.01028  -0.0516   0.7712   0.0125
  -7.500  -0.4967   0.01501   0.00915  -0.0501   0.7704   0.0134
  -7.250  -0.4735   0.01465   0.00877  -0.0494   0.7693   0.0140
  -7.000  -0.4495   0.01438   0.00849  -0.0489   0.7679   0.0148
  -6.750  -0.4256   0.01407   0.00814  -0.0482   0.7665   0.0155
  -6.500  -0.4011   0.01384   0.00787  -0.0477   0.7654   0.0161
  -6.250  -0.3799   0.01319   0.00717  -0.0466   0.7642   0.0175
  -6.000  -0.3552   0.01295   0.00692  -0.0462   0.7633   0.0186
  -5.750  -0.3303   0.01269   0.00663  -0.0457   0.7623   0.0198
  -5.500  -0.3061   0.01233   0.00624  -0.0451   0.7615   0.0215
  -5.250  -0.2816   0.01202   0.00592  -0.0446   0.7607   0.0235
  -5.000  -0.2560   0.01182   0.00570  -0.0443   0.7601   0.0253
  -4.750  -0.2318   0.01148   0.00533  -0.0437   0.7594   0.0282
  -4.500  -0.2063   0.01125   0.00510  -0.0433   0.7588   0.0312
  -4.250  -0.1811   0.01099   0.00482  -0.0429   0.7581   0.0348
  -4.000  -0.1557   0.01079   0.00463  -0.0425   0.7574   0.0396
  -3.750  -0.1307   0.01061   0.00445  -0.0420   0.7565   0.0454
  -3.500  -0.1058   0.01050   0.00437  -0.0416   0.7552   0.0511
  -3.250  -0.0814   0.01032   0.00425  -0.0411   0.7535   0.0605
  -3.000  -0.0564   0.01017   0.00414  -0.0406   0.7519   0.0711
  -2.750  -0.0312   0.00999   0.00401  -0.0403   0.7504   0.0849
  -2.500  -0.0058   0.00977   0.00386  -0.0399   0.7491   0.1052
  -2.250   0.0194   0.00951   0.00370  -0.0395   0.7479   0.1349
  -2.000   0.0440   0.00918   0.00352  -0.0390   0.7468   0.1793
  -1.750   0.0667   0.00874   0.00332  -0.0382   0.7457   0.2566
  -1.500   0.0817   0.00794   0.00309  -0.0359   0.7446   0.4332
  -1.250   0.0873   0.00707   0.00287  -0.0314   0.7433   0.6294
  -1.000   0.0872   0.00629   0.00289  -0.0251   0.7412   0.8326
  -0.750   0.1183   0.00642   0.00315  -0.0256   0.7390   0.8922
  -0.500   0.1437   0.00650   0.00323  -0.0249   0.7367   0.9065
  -0.250   0.1709   0.00658   0.00328  -0.0246   0.7348   0.9160
   0.000   0.1994   0.00674   0.00342  -0.0245   0.7331   0.9261
   0.250   0.2448   0.00700   0.00365  -0.0281   0.7318   0.9318
   0.500   0.3047   0.00734   0.00394  -0.0349   0.7306   0.9349
   0.750   0.3635   0.00757   0.00413  -0.0417   0.7292   0.9363
   1.000   0.3928   0.00783   0.00438  -0.0418   0.7269   0.9440
   1.250   0.4427   0.00795   0.00451  -0.0468   0.7243   0.9448
   1.500   0.4784   0.00791   0.00447  -0.0487   0.7215   0.9455
   1.750   0.5136   0.00786   0.00440  -0.0504   0.7189   0.9462
   2.000   0.5479   0.00779   0.00432  -0.0520   0.7161   0.9470
   2.250   0.5812   0.00777   0.00428  -0.0534   0.7130   0.9479
   2.500   0.6129   0.00776   0.00431  -0.0545   0.7092   0.9491
   2.750   0.6434   0.00773   0.00428  -0.0553   0.7048   0.9505
   3.000   0.6716   0.00767   0.00421  -0.0555   0.7006   0.9521
   3.250   0.6926   0.00766   0.00423  -0.0542   0.6955   0.9550
   3.500   0.7050   0.00761   0.00419  -0.0510   0.6889   0.9586
   3.750   0.7358   0.00755   0.00414  -0.0519   0.6830   0.9591
   4.000   0.7670   0.00753   0.00414  -0.0529   0.6753   0.9597
   4.250   0.7978   0.00751   0.00413  -0.0538   0.6667   0.9603
   4.500   0.8270   0.00752   0.00411  -0.0544   0.6550   0.9610
   4.750   0.8546   0.00755   0.00414  -0.0546   0.6405   0.9617
   5.000   0.8785   0.00773   0.00421  -0.0541   0.6064   0.9630
   5.250   0.8959   0.00813   0.00441  -0.0523   0.5587   0.9650
   5.500   0.9023   0.00868   0.00473  -0.0483   0.5070   0.9681
   5.750   0.9016   0.00911   0.00503  -0.0427   0.4727   0.9720
   6.250   0.9392   0.01032   0.00583  -0.0409   0.3800   0.9744
   6.500   0.9549   0.01104   0.00634  -0.0395   0.3333   0.9761
   6.750   0.9669   0.01175   0.00687  -0.0374   0.2929   0.9785
   7.000   0.9651   0.01242   0.00741  -0.0324   0.2621   0.9822
   7.250   0.9665   0.01317   0.00800  -0.0286   0.2256   0.9850
   7.500   0.9718   0.01440   0.00896  -0.0267   0.1744   0.9874
   7.750   0.9768   0.01552   0.00984  -0.0244   0.1300   0.9897
   8.000   0.9754   0.01689   0.01090  -0.0211   0.0763   0.9923
   8.250   0.9798   0.01807   0.01186  -0.0185   0.0391   0.9942
   8.500   0.9952   0.01898   0.01268  -0.0178   0.0244   0.9952
   8.750   1.0133   0.01964   0.01335  -0.0174   0.0206   0.9962
   9.000   1.0300   0.02039   0.01409  -0.0167   0.0176   0.9972
   9.250   1.0481   0.02105   0.01479  -0.0162   0.0158   0.9981
   9.500   1.0662   0.02174   0.01552  -0.0158   0.0146   0.9989
   9.750   1.0817   0.02266   0.01646  -0.0152   0.0132   0.9997
  10.000   1.0928   0.02350   0.01735  -0.0136   0.0126   1.0000
  10.250   1.0992   0.02414   0.01803  -0.0108   0.0120   1.0000
  10.500   1.1048   0.02481   0.01874  -0.0080   0.0115   1.0000
  10.750   1.1098   0.02551   0.01948  -0.0051   0.0111   1.0000
  11.000   1.1148   0.02619   0.02019  -0.0023   0.0106   1.0000
  11.250   1.1115   0.02729   0.02133   0.0016   0.0098   1.0000
  11.500   1.1088   0.02840   0.02251   0.0053   0.0097   1.0000
  11.750   1.1140   0.02916   0.02331   0.0079   0.0094   1.0000
  12.000   1.1199   0.03016   0.02436   0.0101   0.0092   1.0000
  12.250   1.1272   0.03128   0.02554   0.0118   0.0089   1.0000
  12.500   1.1351   0.03250   0.02682   0.0133   0.0086   1.0000
  12.750   1.1456   0.03361   0.02796   0.0144   0.0082   1.0000
  13.000   1.1551   0.03481   0.02921   0.0154   0.0078   1.0000
  13.250   1.1630   0.03621   0.03065   0.0166   0.0076   1.0000
  13.500   1.1661   0.03806   0.03258   0.0180   0.0075   1.0000
  13.750   1.1622   0.04056   0.03517   0.0196   0.0071   1.0000
  14.000   1.1653   0.04253   0.03722   0.0208   0.0069   1.0000
  14.250   1.1700   0.04442   0.03920   0.0217   0.0068   1.0000
  14.500   1.1744   0.04637   0.04121   0.0225   0.0068   1.0000
  14.750   1.1852   0.04782   0.04274   0.0228   0.0065   1.0000
  15.000   1.1871   0.05010   0.04512   0.0236   0.0064   1.0000
  15.250   1.1939   0.05199   0.04708   0.0239   0.0062   1.0000
  15.500   1.1920   0.05474   0.04994   0.0248   0.0063   1.0000
  15.750   1.1974   0.05690   0.05217   0.0249   0.0060   1.0000
  16.000   1.1976   0.05958   0.05495   0.0253   0.0060   1.0000
  16.250   1.2012   0.06203   0.05748   0.0252   0.0058   1.0000
  16.500   1.2012   0.06489   0.06043   0.0252   0.0057   1.0000
  16.750   1.2072   0.06728   0.06285   0.0245   0.0054   1.0000
  17.000   1.2000   0.07100   0.06674   0.0249   0.0056   1.0000
  17.250   1.1986   0.07425   0.07009   0.0245   0.0055   1.0000
  17.500   1.2002   0.07733   0.07319   0.0234   0.0052   1.0000
  17.750   1.1952   0.08116   0.07716   0.0229   0.0053   1.0000
  18.000   1.1787   0.08651   0.08265   0.0222   0.0050   1.0000
  18.250   1.1576   0.09262   0.08897   0.0214   0.0049   1.0000
  18.500   1.1748   0.09399   0.09033   0.0198   0.0052   1.0000
  18.750   1.1486   0.10121   0.09776   0.0182   0.0049   1.0000
  19.000   1.1372   0.10680   0.10350   0.0160   0.0049   1.0000
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