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AH 85-L-120/17 (ah85l120-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: AH 85-L-120/17 (ah85l120-il)
Reynolds number: 100,000
Max Cl/Cd: 29.76 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ah85l120-il-100000-n5.txt
Download as CSV file: xf-ah85l120-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.6175   0.09111   0.08619  -0.0392   1.0000   0.0229
 -11.500  -0.6399   0.08192   0.07694  -0.0454   1.0000   0.0221
 -11.250  -0.6638   0.07501   0.06993  -0.0492   1.0000   0.0218
 -11.000  -0.6884   0.06938   0.06416  -0.0509   1.0000   0.0216
 -10.750  -0.7109   0.06479   0.05940  -0.0508   1.0000   0.0214
 -10.500  -0.7310   0.06095   0.05537  -0.0494   1.0000   0.0211
 -10.250  -0.7490   0.05769   0.05192  -0.0469   1.0000   0.0210
 -10.000  -0.7666   0.05480   0.04883  -0.0432   1.0000   0.0210
  -9.750  -0.7833   0.05216   0.04593  -0.0386   1.0000   0.0207
  -9.500  -0.7951   0.04977   0.04332  -0.0341   1.0000   0.0208
  -9.250  -0.8067   0.04776   0.04109  -0.0291   1.0000   0.0209
  -9.000  -0.8187   0.04594   0.03902  -0.0236   1.0000   0.0206
  -8.750  -0.8277   0.04420   0.03707  -0.0184   1.0000   0.0210
  -8.500  -0.8305   0.04219   0.03477  -0.0141   0.9994   0.0211
  -8.250  -0.8155   0.03946   0.03164  -0.0132   0.9945   0.0214
  -8.000  -0.7961   0.03681   0.02859  -0.0127   0.9907   0.0220
  -7.750  -0.7750   0.03501   0.02647  -0.0124   0.9868   0.0244
  -7.500  -0.7503   0.03298   0.02409  -0.0124   0.9838   0.0255
  -7.250  -0.7223   0.03099   0.02170  -0.0127   0.9818   0.0266
  -7.000  -0.6951   0.02927   0.01972  -0.0127   0.9796   0.0275
  -6.750  -0.6689   0.02726   0.01762  -0.0128   0.9775   0.0286
  -6.500  -0.6450   0.02580   0.01613  -0.0128   0.9746   0.0304
  -6.250  -0.6202   0.02473   0.01498  -0.0129   0.9718   0.0347
  -6.000  -0.5953   0.02386   0.01393  -0.0129   0.9693   0.0384
  -5.750  -0.5801   0.02276   0.01281  -0.0112   0.9650   0.0424
  -5.500  -0.5581   0.02195   0.01184  -0.0107   0.9615   0.0497
  -5.250  -0.5354   0.02096   0.01093  -0.0104   0.9587   0.0666
  -5.000  -0.5156   0.01983   0.01013  -0.0097   0.9558   0.1193
  -4.750  -0.5095   0.01845   0.00959  -0.0067   0.9505   0.2620
  -4.500  -0.5031   0.01697   0.00920  -0.0034   0.9462   0.4598
  -4.250  -0.4723   0.01729   0.01059  -0.0015   0.9456   0.6804
  -4.000  -0.4450   0.01818   0.01142   0.0001   0.9433   0.7454
  -3.750  -0.4237   0.01879   0.01188   0.0022   0.9394   0.7669
  -3.500  -0.4020   0.01920   0.01212   0.0039   0.9355   0.7847
  -3.250  -0.3735   0.01962   0.01236   0.0043   0.9327   0.8003
  -3.000  -0.3371   0.02010   0.01265   0.0032   0.9311   0.8122
  -2.750  -0.3003   0.02046   0.01286   0.0018   0.9296   0.8225
  -2.500  -0.2825   0.02062   0.01292   0.0038   0.9249   0.8332
  -2.250  -0.2534   0.02073   0.01289   0.0035   0.9216   0.8402
  -2.000  -0.2253   0.02073   0.01278   0.0032   0.9183   0.8472
  -1.750  -0.1874   0.02078   0.01273   0.0010   0.9165   0.8515
  -1.500  -0.1739   0.02075   0.01263   0.0034   0.9109   0.8600
  -1.250  -0.1406   0.02080   0.01261   0.0021   0.9076   0.8637
  -1.000  -0.1101   0.02079   0.01253   0.0012   0.9044   0.8689
  -0.750  -0.0798   0.02073   0.01243   0.0003   0.9015   0.8743
  -0.500  -0.0550   0.02080   0.01247   0.0006   0.8962   0.8784
  -0.250  -0.0297   0.02078   0.01243   0.0007   0.8916   0.8837
   0.000   0.0001   0.02073   0.01237   0.0000   0.8883   0.8883
   0.250   0.0298   0.02078   0.01243  -0.0007   0.8837   0.8916
   0.500   0.0549   0.02080   0.01247  -0.0006   0.8784   0.8963
   0.750   0.0801   0.02073   0.01243  -0.0004   0.8743   0.9015
   1.000   0.1098   0.02079   0.01254  -0.0011   0.8689   0.9043
   1.250   0.1404   0.02081   0.01261  -0.0020   0.8637   0.9076
   1.500   0.1737   0.02076   0.01264  -0.0034   0.8601   0.9110
   1.750   0.1877   0.02079   0.01273  -0.0010   0.8515   0.9165
   2.000   0.2252   0.02073   0.01278  -0.0031   0.8472   0.9183
   2.250   0.2532   0.02073   0.01288  -0.0035   0.8400   0.9215
   2.500   0.2828   0.02061   0.01290  -0.0038   0.8332   0.9248
   2.750   0.3006   0.02046   0.01286  -0.0019   0.8226   0.9296
   3.000   0.3377   0.02011   0.01266  -0.0033   0.8125   0.9311
   3.250   0.3741   0.01962   0.01233  -0.0043   0.8005   0.9327
   3.500   0.4026   0.01920   0.01212  -0.0040   0.7851   0.9355
   3.750   0.4237   0.01877   0.01185  -0.0022   0.7664   0.9394
   4.000   0.4444   0.01819   0.01143   0.0000   0.7446   0.9434
   4.250   0.4722   0.01734   0.01067   0.0014   0.6851   0.9456
   4.500   0.5039   0.01693   0.00921   0.0033   0.4661   0.9462
   4.750   0.5097   0.01845   0.00959   0.0066   0.2615   0.9506
   5.000   0.5166   0.01977   0.01012   0.0096   0.1251   0.9557
   5.250   0.5348   0.02106   0.01097   0.0105   0.0636   0.9587
   5.500   0.5584   0.02194   0.01183   0.0106   0.0488   0.9615
   5.750   0.5802   0.02279   0.01280   0.0113   0.0418   0.9650
   6.000   0.5955   0.02387   0.01396   0.0130   0.0379   0.9693
   6.250   0.6203   0.02473   0.01499   0.0129   0.0330   0.9718
   6.500   0.6450   0.02582   0.01614   0.0128   0.0303   0.9746
   6.750   0.6691   0.02726   0.01763   0.0129   0.0287   0.9774
   7.000   0.6954   0.02931   0.01978   0.0128   0.0272   0.9796
   7.250   0.7225   0.03102   0.02174   0.0127   0.0266   0.9818
   7.500   0.7504   0.03296   0.02407   0.0124   0.0253   0.9839
   7.750   0.7748   0.03486   0.02633   0.0125   0.0236   0.9870
   8.000   0.7960   0.03680   0.02856   0.0127   0.0218   0.9907
   8.250   0.8153   0.03939   0.03154   0.0132   0.0211   0.9945
   8.500   0.8304   0.04219   0.03474   0.0141   0.0209   0.9995
   8.750   0.8275   0.04414   0.03695   0.0183   0.0206   1.0000
   9.000   0.8185   0.04593   0.03899   0.0236   0.0205   1.0000
   9.250   0.8068   0.04775   0.04107   0.0291   0.0207   1.0000
   9.500   0.7955   0.04972   0.04326   0.0340   0.0207   1.0000
   9.750   0.7825   0.05227   0.04604   0.0387   0.0207   1.0000
  10.000   0.7682   0.05468   0.04864   0.0430   0.0207   1.0000
  10.250   0.7502   0.05758   0.05179   0.0468   0.0209   1.0000
  10.500   0.7319   0.06087   0.05527   0.0493   0.0210   1.0000
  10.750   0.7096   0.06498   0.05958   0.0508   0.0213   1.0000
  11.000   0.6888   0.06937   0.06413   0.0508   0.0215   1.0000
  11.250   0.6631   0.07519   0.07010   0.0491   0.0217   1.0000
  11.500   0.6394   0.08217   0.07719   0.0452   0.0222   1.0000
  11.750   0.6173   0.09137   0.08643   0.0389   0.0226   1.0000
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