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USA 35 A AIRFOIL (usa35a-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: USA 35 A AIRFOIL (usa35a-il)
Reynolds number: 100,000
Max Cl/Cd: 46.39 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa35a-il-100000-n5.txt
Download as CSV file: xf-usa35a-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 35 A AIRFOIL                                
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750   0.0702   0.11069   0.10537  -0.0934   0.8765   0.0816
 -10.500   0.0919   0.10773   0.10241  -0.0923   0.8650   0.0827
 -10.000   0.0157   0.10834   0.10284  -0.0912   0.8871   0.0820
  -9.500   0.0429   0.10297   0.09742  -0.0916   0.8658   0.0840
  -9.000   0.0309   0.09162   0.08593  -0.0980   0.8452   0.0622
  -8.750   0.0422   0.08913   0.08338  -0.0981   0.8355   0.0616
  -8.500   0.0481   0.08625   0.08050  -0.0989   0.8236   0.0608
  -8.250   0.0521   0.08289   0.07708  -0.1003   0.8140   0.0601
  -8.000   0.0534   0.07945   0.07364  -0.1019   0.8023   0.0599
  -7.750   0.0543   0.07577   0.06990  -0.1039   0.7932   0.0601
  -7.500   0.0520   0.07200   0.06614  -0.1061   0.7813   0.0603
  -7.250   0.0462   0.06774   0.06182  -0.1090   0.7723   0.0602
  -7.000   0.0402   0.06206   0.05609  -0.1147   0.7609   0.0599
  -6.750   0.0282   0.05289   0.04662  -0.1228   0.7525   0.0591
  -6.500   0.0201   0.04528   0.03855  -0.1269   0.7430   0.0591
  -6.250   0.0261   0.04064   0.03342  -0.1283   0.7338   0.0596
  -6.000   0.0387   0.03697   0.02921  -0.1289   0.7254   0.0609
  -5.750   0.0528   0.03382   0.02543  -0.1288   0.7154   0.0626
  -5.500   0.0783   0.03296   0.02447  -0.1288   0.7077   0.0636
  -5.250   0.0995   0.03178   0.02312  -0.1283   0.6978   0.0648
  -5.000   0.1231   0.03024   0.02121  -0.1281   0.6900   0.0661
  -4.750   0.1472   0.02868   0.01920  -0.1279   0.6828   0.0677
  -4.500   0.1715   0.02786   0.01823  -0.1275   0.6742   0.0692
  -4.250   0.1984   0.02722   0.01747  -0.1274   0.6674   0.0713
  -4.000   0.2237   0.02641   0.01639  -0.1270   0.6596   0.0738
  -3.750   0.2494   0.02573   0.01557  -0.1267   0.6523   0.0757
  -3.500   0.2772   0.02515   0.01487  -0.1266   0.6466   0.0778
  -3.250   0.3033   0.02465   0.01418  -0.1262   0.6399   0.0809
  -3.000   0.3292   0.02422   0.01374  -0.1259   0.6330   0.0836
  -2.750   0.3569   0.02378   0.01318  -0.1258   0.6273   0.0869
  -2.500   0.3838   0.02339   0.01269  -0.1255   0.6216   0.0904
  -2.250   0.4090   0.02311   0.01243  -0.1250   0.6144   0.0941
  -2.000   0.4362   0.02276   0.01194  -0.1247   0.6079   0.0983
  -1.750   0.4628   0.02247   0.01165  -0.1244   0.6016   0.1028
  -1.500   0.4877   0.02226   0.01141  -0.1238   0.5942   0.1077
  -1.250   0.5142   0.02201   0.01117  -0.1235   0.5883   0.1133
  -1.000   0.5426   0.02178   0.01086  -0.1235   0.5836   0.1199
  -0.750   0.5668   0.02171   0.01084  -0.1228   0.5776   0.1276
  -0.500   0.5924   0.02159   0.01078  -0.1224   0.5719   0.1370
  -0.250   0.6196   0.02146   0.01068  -0.1223   0.5670   0.1505
   0.000   0.6482   0.02134   0.01057  -0.1223   0.5627   0.1732
   0.250   0.6719   0.02131   0.01072  -0.1217   0.5569   0.2104
   0.750   0.7231   0.02093   0.01089  -0.1211   0.5468   0.3736
   1.000   0.7501   0.02062   0.01092  -0.1208   0.5427   0.5218
   1.250   0.7651   0.02021   0.01129  -0.1177   0.5376   0.7488
   1.500   0.8034   0.02011   0.01141  -0.1192   0.5314   1.0000
   1.750   0.8292   0.02034   0.01147  -0.1188   0.5263   1.0000
   2.000   0.8574   0.02056   0.01147  -0.1188   0.5220   1.0000
   2.250   0.8803   0.02091   0.01175  -0.1180   0.5170   1.0000
   2.500   0.9025   0.02125   0.01204  -0.1171   0.5113   1.0000
   2.750   0.9273   0.02153   0.01220  -0.1166   0.5061   1.0000
   3.000   0.9547   0.02176   0.01227  -0.1165   0.5015   1.0000
   3.250   0.9771   0.02213   0.01258  -0.1156   0.4961   1.0000
   3.500   0.9974   0.02252   0.01296  -0.1145   0.4901   1.0000
   3.750   1.0213   0.02283   0.01319  -0.1139   0.4848   1.0000
   4.000   1.0483   0.02308   0.01331  -0.1137   0.4805   1.0000
   4.250   1.0685   0.02352   0.01374  -0.1126   0.4752   1.0000
   4.500   1.0870   0.02397   0.01421  -0.1112   0.4691   1.0000
   4.750   1.1099   0.02428   0.01446  -0.1105   0.4639   1.0000
   5.000   1.1369   0.02451   0.01455  -0.1103   0.4596   1.0000
   5.250   1.1504   0.02511   0.01523  -0.1082   0.4532   1.0000
   5.500   1.1685   0.02557   0.01569  -0.1068   0.4475   1.0000
   5.750   1.1914   0.02589   0.01594  -0.1062   0.4430   1.0000
   6.000   1.2134   0.02628   0.01628  -0.1053   0.4387   1.0000
   6.250   1.2235   0.02698   0.01706  -0.1029   0.4326   1.0000
   6.500   1.2393   0.02744   0.01752  -0.1011   0.4274   1.0000
   6.750   1.2620   0.02771   0.01770  -0.1004   0.4231   1.0000
   7.000   1.2700   0.02849   0.01855  -0.0977   0.4171   1.0000
   7.250   1.2810   0.02920   0.01928  -0.0955   0.4113   1.0000
   7.500   1.2998   0.02957   0.01959  -0.0944   0.4064   1.0000
   7.750   1.3099   0.03037   0.02042  -0.0923   0.4006   1.0000
   8.000   1.3170   0.03130   0.02140  -0.0899   0.3941   1.0000
   8.250   1.3346   0.03172   0.02174  -0.0887   0.3888   1.0000
   8.500   1.3414   0.03281   0.02287  -0.0866   0.3828   1.0000
   8.750   1.3484   0.03394   0.02406  -0.0846   0.3769   1.0000
   9.000   1.3648   0.03456   0.02463  -0.0835   0.3724   1.0000
   9.250   1.3776   0.03549   0.02556  -0.0822   0.3679   1.0000
   9.500   1.3795   0.03716   0.02734  -0.0802   0.3626   1.0000
   9.750   1.3899   0.03828   0.02848  -0.0788   0.3579   1.0000
  10.000   1.4103   0.03874   0.02887  -0.0782   0.3541   1.0000
  10.250   1.4125   0.04055   0.03077  -0.0764   0.3494   1.0000
  10.500   1.4125   0.04259   0.03291  -0.0747   0.3442   1.0000
  10.750   1.4235   0.04377   0.03410  -0.0737   0.3398   1.0000
  11.000   1.4481   0.04388   0.03411  -0.0733   0.3361   1.0000
  11.250   1.4339   0.04724   0.03767  -0.0712   0.3306   1.0000
  11.500   1.4326   0.04960   0.04011  -0.0699   0.3254   1.0000
  11.750   1.4475   0.05050   0.04099  -0.0692   0.3213   1.0000
  12.000   1.4631   0.05138   0.04186  -0.0685   0.3175   1.0000
  12.250   1.4375   0.05629   0.04700  -0.0669   0.3113   1.0000
  12.500   1.4402   0.05851   0.04928  -0.0661   0.3065   1.0000
  12.750   1.4626   0.05865   0.04935  -0.0656   0.3029   1.0000
  13.000   1.4381   0.06394   0.05483  -0.0647   0.2967   1.0000
  13.250   1.4231   0.06839   0.05941  -0.0641   0.2904   1.0000
  13.500   1.4440   0.06859   0.05958  -0.0636   0.2867   1.0000
  13.750   1.4053   0.07622   0.06743  -0.0636   0.2790   1.0000
  14.000   1.3956   0.08039   0.07168  -0.0636   0.2728   1.0000
  14.250   1.4221   0.07978   0.07101  -0.0630   0.2699   1.0000
  14.500   1.3465   0.09320   0.08474  -0.0646   0.2582   1.0000
  14.750   1.3690   0.09304   0.08456  -0.0641   0.2554   1.0000
  15.000   1.3996   0.09175   0.08321  -0.0634   0.2535   1.0000
  15.500   1.3127   0.11095   0.10273  -0.0670   0.2358   1.0000
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