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AH 85-L-120/17 (ah85l120-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: AH 85-L-120/17 (ah85l120-il)
Reynolds number: 200,000
Max Cl/Cd: 34.99 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ah85l120-il-200000-n5.txt
Download as CSV file: xf-ah85l120-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AH 85-L-120/17                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.6579   0.08635   0.08286  -0.0364   1.0000   0.0117
 -12.000  -0.6769   0.07772   0.07414  -0.0428   1.0000   0.0114
 -11.750  -0.6981   0.07075   0.06705  -0.0472   1.0000   0.0111
 -11.500  -0.7196   0.06493   0.06110  -0.0496   1.0000   0.0112
 -11.250  -0.7402   0.06009   0.05610  -0.0502   1.0000   0.0111
 -11.000  -0.7611   0.05569   0.05150  -0.0495   1.0000   0.0110
 -10.750  -0.7788   0.05197   0.04756  -0.0477   1.0000   0.0112
 -10.500  -0.7930   0.04885   0.04423  -0.0451   1.0000   0.0111
 -10.250  -0.8068   0.04599   0.04115  -0.0416   1.0000   0.0110
 -10.000  -0.8214   0.04357   0.03848  -0.0369   1.0000   0.0113
  -9.750  -0.8145   0.04019   0.03466  -0.0363   0.9780   0.0115
  -9.500  -0.8002   0.03767   0.03161  -0.0361   0.9692   0.0124
  -9.250  -0.7870   0.03414   0.02760  -0.0356   0.9633   0.0128
  -9.000  -0.7660   0.03150   0.02460  -0.0359   0.9593   0.0129
  -8.750  -0.7429   0.02867   0.02148  -0.0364   0.9563   0.0135
  -8.500  -0.7187   0.02695   0.01955  -0.0366   0.9525   0.0139
  -8.250  -0.6927   0.02542   0.01784  -0.0371   0.9491   0.0145
  -8.000  -0.6649   0.02395   0.01619  -0.0377   0.9463   0.0151
  -7.750  -0.6371   0.02277   0.01482  -0.0384   0.9438   0.0165
  -7.500  -0.6111   0.02171   0.01364  -0.0386   0.9411   0.0174
  -7.250  -0.5871   0.02090   0.01271  -0.0384   0.9378   0.0186
  -7.000  -0.5660   0.01966   0.01139  -0.0378   0.9344   0.0197
  -6.750  -0.5459   0.01869   0.01035  -0.0370   0.9309   0.0208
  -6.500  -0.5260   0.01798   0.00957  -0.0361   0.9278   0.0225
  -6.250  -0.5087   0.01742   0.00889  -0.0345   0.9241   0.0253
  -6.000  -0.4892   0.01697   0.00835  -0.0333   0.9206   0.0277
  -5.750  -0.4711   0.01635   0.00769  -0.0319   0.9173   0.0339
  -5.500  -0.4520   0.01582   0.00714  -0.0306   0.9145   0.0443
  -5.250  -0.4378   0.01523   0.00671  -0.0285   0.9107   0.0747
  -5.000  -0.4256   0.01448   0.00631  -0.0261   0.9068   0.1432
  -4.750  -0.4139   0.01369   0.00590  -0.0237   0.9034   0.2333
  -4.500  -0.4062   0.01283   0.00555  -0.0205   0.9000   0.3450
  -4.250  -0.4052   0.01197   0.00532  -0.0157   0.8950   0.4772
  -4.000  -0.3967   0.01136   0.00540  -0.0117   0.8915   0.6152
  -3.750  -0.3711   0.01155   0.00595  -0.0103   0.8895   0.7061
  -3.500  -0.3449   0.01180   0.00616  -0.0096   0.8876   0.7354
  -3.250  -0.3216   0.01202   0.00629  -0.0084   0.8846   0.7528
  -3.000  -0.2988   0.01223   0.00643  -0.0073   0.8813   0.7675
  -2.750  -0.2745   0.01243   0.00656  -0.0064   0.8784   0.7793
  -2.500  -0.2499   0.01264   0.00669  -0.0055   0.8759   0.7909
  -2.250  -0.2262   0.01280   0.00676  -0.0045   0.8736   0.8021
  -2.000  -0.1982   0.01306   0.00699  -0.0043   0.8707   0.8078
  -1.750  -0.1779   0.01310   0.00697  -0.0029   0.8666   0.8151
  -1.500  -0.1508   0.01317   0.00700  -0.0028   0.8637   0.8191
  -1.250  -0.1229   0.01323   0.00701  -0.0027   0.8612   0.8229
  -1.000  -0.0979   0.01321   0.00693  -0.0023   0.8588   0.8283
  -0.750  -0.0766   0.01326   0.00697  -0.0011   0.8538   0.8326
  -0.500  -0.0499   0.01330   0.00701  -0.0009   0.8503   0.8357
  -0.250  -0.0237   0.01329   0.00698  -0.0007   0.8474   0.8396
   0.000   0.0000   0.01322   0.00686   0.0000   0.8449   0.8449
   0.250   0.0237   0.01330   0.00698   0.0007   0.8397   0.8474
   0.500   0.0499   0.01330   0.00701   0.0010   0.8357   0.8504
   0.750   0.0765   0.01326   0.00698   0.0012   0.8326   0.8539
   1.000   0.0982   0.01321   0.00693   0.0022   0.8284   0.8587
   1.250   0.1229   0.01323   0.00701   0.0027   0.8230   0.8612
   1.500   0.1509   0.01317   0.00700   0.0028   0.8191   0.8637
   1.750   0.1778   0.01310   0.00697   0.0030   0.8151   0.8667
   2.000   0.1983   0.01304   0.00697   0.0043   0.8074   0.8706
   2.250   0.2263   0.01279   0.00675   0.0045   0.8021   0.8735
   2.500   0.2500   0.01264   0.00669   0.0055   0.7909   0.8758
   2.750   0.2746   0.01244   0.00658   0.0064   0.7797   0.8785
   3.000   0.2988   0.01223   0.00643   0.0073   0.7675   0.8814
   3.250   0.3216   0.01203   0.00630   0.0085   0.7532   0.8847
   3.500   0.3449   0.01180   0.00616   0.0096   0.7353   0.8876
   3.750   0.3709   0.01157   0.00598   0.0103   0.7077   0.8895
   4.000   0.3971   0.01135   0.00544   0.0116   0.6228   0.8915
   4.250   0.4060   0.01194   0.00533   0.0156   0.4818   0.8950
   4.500   0.4074   0.01279   0.00555   0.0203   0.3512   0.8999
   4.750   0.4137   0.01369   0.00590   0.0237   0.2329   0.9034
   5.000   0.4258   0.01446   0.00630   0.0261   0.1453   0.9068
   5.250   0.4368   0.01529   0.00673   0.0286   0.0682   0.9109
   5.500   0.4521   0.01581   0.00714   0.0306   0.0443   0.9145
   5.750   0.4711   0.01635   0.00770   0.0319   0.0340   0.9173
   6.000   0.4890   0.01699   0.00836   0.0334   0.0276   0.9206
   6.250   0.5085   0.01744   0.00892   0.0346   0.0243   0.9241
   6.500   0.5259   0.01798   0.00957   0.0362   0.0226   0.9278
   6.750   0.5460   0.01867   0.01035   0.0371   0.0212   0.9310
   7.000   0.5650   0.01981   0.01154   0.0380   0.0193   0.9345
   7.250   0.5870   0.02096   0.01277   0.0384   0.0186   0.9378
   7.500   0.6110   0.02167   0.01360   0.0386   0.0172   0.9412
   7.750   0.6369   0.02268   0.01474   0.0384   0.0162   0.9439
   8.000   0.6647   0.02397   0.01621   0.0378   0.0148   0.9464
   8.250   0.6920   0.02536   0.01775   0.0372   0.0141   0.9493
   8.500   0.7183   0.02695   0.01953   0.0367   0.0137   0.9526
   8.750   0.7419   0.02897   0.02174   0.0364   0.0131   0.9563
   9.000   0.7649   0.03201   0.02514   0.0360   0.0127   0.9593
   9.250   0.7853   0.03473   0.02824   0.0358   0.0127   0.9633
   9.500   0.7988   0.03832   0.03227   0.0361   0.0126   0.9691
   9.750   0.8114   0.04098   0.03543   0.0364   0.0121   0.9782
  10.000   0.8153   0.04435   0.03923   0.0375   0.0118   1.0000
  10.250   0.8050   0.04622   0.04137   0.0418   0.0112   1.0000
  10.500   0.7904   0.04914   0.04454   0.0453   0.0111   1.0000
  10.750   0.7745   0.05249   0.04811   0.0479   0.0110   1.0000
  11.000   0.7600   0.05583   0.05162   0.0495   0.0113   1.0000
  11.250   0.7369   0.06059   0.05661   0.0502   0.0110   1.0000
  11.500   0.7187   0.06514   0.06128   0.0495   0.0111   1.0000
  11.750   0.6969   0.07099   0.06729   0.0470   0.0112   1.0000
  12.000   0.6748   0.07817   0.07457   0.0424   0.0116   1.0000
  12.250   0.6619   0.08423   0.08065   0.0383   0.0123   1.0000
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