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USA 35 AIRFOIL (usa35-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: USA 35 AIRFOIL (usa35-il)
Reynolds number: 100,000
Max Cl/Cd: 46.36 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa35-il-100000-n5.txt
Download as CSV file: xf-usa35-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 35 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500   0.0103   0.11465   0.10916  -0.0864   0.9087   0.0808
 -10.250   0.0114   0.11144   0.10592  -0.0895   0.8988   0.0820
 -10.000   0.0087   0.10825   0.10273  -0.0923   0.8866   0.0823
  -9.250   0.0505   0.10017   0.09459  -0.0924   0.8549   0.0858
  -8.750   0.0374   0.08860   0.08285  -0.0989   0.8349   0.0627
  -8.500   0.0459   0.08599   0.08023  -0.0993   0.8238   0.0620
  -8.250   0.0511   0.08286   0.07706  -0.1004   0.8140   0.0613
  -8.000   0.0532   0.07944   0.07363  -0.1019   0.8029   0.0606
  -7.750   0.0538   0.07573   0.06987  -0.1039   0.7933   0.0604
  -7.500   0.0519   0.07197   0.06610  -0.1061   0.7818   0.0607
  -7.250   0.0458   0.06777   0.06185  -0.1090   0.7722   0.0608
  -7.000   0.0402   0.06212   0.05614  -0.1147   0.7609   0.0607
  -6.750   0.0320   0.05382   0.04756  -0.1221   0.7530   0.0602
  -6.500   0.0225   0.04616   0.03949  -0.1264   0.7422   0.0601
  -6.250   0.0278   0.04109   0.03389  -0.1281   0.7338   0.0605
  -6.000   0.0383   0.03736   0.02964  -0.1286   0.7243   0.0615
  -5.750   0.0529   0.03405   0.02564  -0.1287   0.7154   0.0632
  -5.500   0.0775   0.03325   0.02479  -0.1285   0.7075   0.0642
  -5.250   0.0993   0.03207   0.02343  -0.1281   0.6980   0.0655
  -5.000   0.1234   0.03048   0.02145  -0.1280   0.6909   0.0668
  -4.750   0.1461   0.02899   0.01956  -0.1276   0.6822   0.0682
  -4.500   0.1710   0.02799   0.01833  -0.1273   0.6741   0.0697
  -4.250   0.1980   0.02736   0.01759  -0.1272   0.6674   0.0716
  -4.000   0.2225   0.02663   0.01666  -0.1268   0.6593   0.0739
  -3.750   0.2492   0.02582   0.01560  -0.1265   0.6528   0.0759
  -3.500   0.2767   0.02525   0.01494  -0.1264   0.6469   0.0777
  -3.250   0.3018   0.02479   0.01439  -0.1260   0.6394   0.0804
  -3.000   0.3288   0.02428   0.01372  -0.1257   0.6331   0.0833
  -2.500   0.3822   0.02351   0.01280  -0.1252   0.6211   0.0892
  -2.250   0.4083   0.02315   0.01243  -0.1248   0.6144   0.0925
  -2.000   0.4366   0.02279   0.01196  -0.1247   0.6086   0.0964
  -1.750   0.4610   0.02254   0.01172  -0.1241   0.6011   0.1002
  -1.500   0.4868   0.02230   0.01147  -0.1236   0.5943   0.1048
  -1.250   0.5148   0.02203   0.01112  -0.1235   0.5890   0.1098
  -1.000   0.5401   0.02190   0.01101  -0.1230   0.5831   0.1159
  -0.750   0.5653   0.02177   0.01092  -0.1225   0.5772   0.1226
  -0.500   0.5922   0.02163   0.01076  -0.1223   0.5721   0.1316
  -0.250   0.6208   0.02148   0.01058  -0.1223   0.5677   0.1447
   0.000   0.6451   0.02143   0.01068  -0.1217   0.5622   0.1642
   0.250   0.6703   0.02134   0.01074  -0.1213   0.5567   0.2019
   0.500   0.6967   0.02117   0.01076  -0.1211   0.5518   0.2663
   0.750   0.7245   0.02091   0.01077  -0.1212   0.5474   0.3701
   1.000   0.7468   0.02065   0.01104  -0.1203   0.5422   0.5214
   1.250   0.7626   0.02023   0.01135  -0.1173   0.5369   0.7426
   1.500   0.8033   0.02009   0.01136  -0.1191   0.5315   1.0000
   1.750   0.8311   0.02030   0.01137  -0.1190   0.5272   1.0000
   2.000   0.8554   0.02061   0.01156  -0.1184   0.5223   1.0000
   2.250   0.8773   0.02095   0.01184  -0.1175   0.5164   1.0000
   2.500   0.9020   0.02122   0.01199  -0.1169   0.5111   1.0000
   2.750   0.9293   0.02145   0.01205  -0.1168   0.5064   1.0000
   3.000   0.9529   0.02179   0.01231  -0.1161   0.5014   1.0000
   3.250   0.9734   0.02219   0.01269  -0.1150   0.4956   1.0000
   3.500   0.9972   0.02250   0.01293  -0.1144   0.4904   1.0000
   3.750   1.0238   0.02276   0.01306  -0.1141   0.4859   1.0000
   4.000   1.0460   0.02314   0.01339  -0.1133   0.4807   1.0000
   4.250   1.0643   0.02358   0.01385  -0.1119   0.4744   1.0000
   4.500   1.0871   0.02390   0.01411  -0.1111   0.4690   1.0000
   4.750   1.1138   0.02414   0.01421  -0.1109   0.4646   1.0000
   5.000   1.1299   0.02468   0.01480  -0.1092   0.4588   1.0000
   5.250   1.1480   0.02515   0.01529  -0.1078   0.4531   1.0000
   5.500   1.1706   0.02548   0.01556  -0.1071   0.4483   1.0000
   5.750   1.1952   0.02578   0.01576  -0.1066   0.4441   1.0000
   6.000   1.2054   0.02647   0.01655  -0.1041   0.4376   1.0000
   6.250   1.2221   0.02693   0.01700  -0.1025   0.4323   1.0000
   6.500   1.2445   0.02722   0.01721  -0.1017   0.4280   1.0000
   6.750   1.2563   0.02787   0.01791  -0.0995   0.4228   1.0000
   7.000   1.2664   0.02860   0.01868  -0.0971   0.4170   1.0000
   7.250   1.2841   0.02901   0.01905  -0.0958   0.4119   1.0000
   7.500   1.2993   0.02956   0.01957  -0.0942   0.4066   1.0000
   7.750   1.3044   0.03055   0.02063  -0.0915   0.4000   1.0000
   8.000   1.3201   0.03105   0.02109  -0.0901   0.3945   1.0000
   8.250   1.3320   0.03181   0.02185  -0.0883   0.3889   1.0000
   8.500   1.3368   0.03299   0.02309  -0.0860   0.3825   1.0000
   8.750   1.3521   0.03362   0.02368  -0.0847   0.3774   1.0000
   9.000   1.3658   0.03445   0.02450  -0.0834   0.3728   1.0000
   9.250   1.3687   0.03599   0.02615  -0.0813   0.3673   1.0000
   9.500   1.3797   0.03705   0.02721  -0.0800   0.3627   1.0000
   9.750   1.4003   0.03748   0.02757  -0.0793   0.3589   1.0000
  10.000   1.4017   0.03928   0.02948  -0.0774   0.3539   1.0000
  10.250   1.4039   0.04109   0.03137  -0.0758   0.3487   1.0000
  10.500   1.4166   0.04211   0.03238  -0.0747   0.3443   1.0000
  10.750   1.4397   0.04238   0.03256  -0.0743   0.3407   1.0000
  11.000   1.4268   0.04555   0.03594  -0.0721   0.3352   1.0000
  11.250   1.4286   0.04759   0.03805  -0.0708   0.3304   1.0000
  11.500   1.4442   0.04843   0.03887  -0.0701   0.3264   1.0000
  11.750   1.4570   0.04957   0.04000  -0.0693   0.3223   1.0000
  12.000   1.4364   0.05385   0.04448  -0.0676   0.3163   1.0000
  12.250   1.4412   0.05578   0.04646  -0.0667   0.3115   1.0000
  12.500   1.4651   0.05578   0.04638  -0.0662   0.3078   1.0000
  12.750   1.4387   0.06111   0.05193  -0.0651   0.3016   1.0000
  13.000   1.4289   0.06483   0.05575  -0.0644   0.2957   1.0000
  13.250   1.4488   0.06519   0.05607  -0.0639   0.2920   1.0000
  13.500   1.4274   0.07048   0.06152  -0.0635   0.2859   1.0000
  13.750   1.4036   0.07629   0.06749  -0.0634   0.2789   1.0000
  14.000   1.4264   0.07622   0.06739  -0.0629   0.2756   1.0000
  14.250   1.3593   0.08819   0.07963  -0.0640   0.2650   1.0000
  14.500   1.3751   0.08900   0.08045  -0.0636   0.2612   1.0000
  14.750   1.4057   0.08773   0.07912  -0.0630   0.2589   1.0000
  15.250   1.3558   0.10100   0.09263  -0.0647   0.2446   1.0000
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