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USA-35B AIRFOIL (usa35b-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: USA-35B AIRFOIL (usa35b-il)
Reynolds number: 500,000
Max Cl/Cd: 96.97 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa35b-il-500000-n5.txt
Download as CSV file: xf-usa35b-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA-35B AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.3843   0.10561   0.10307  -0.0304   1.0000   0.0218
 -11.250  -0.5699   0.03223   0.02854  -0.0902   0.9664   0.0248
 -11.000  -0.5537   0.02855   0.02451  -0.0921   0.9584   0.0250
 -10.750  -0.5335   0.02662   0.02237  -0.0926   0.9498   0.0252
 -10.500  -0.5105   0.02508   0.02066  -0.0930   0.9422   0.0254
 -10.250  -0.4882   0.02380   0.01921  -0.0930   0.9329   0.0256
 -10.000  -0.4645   0.02275   0.01801  -0.0929   0.9244   0.0259
  -9.750  -0.4408   0.02178   0.01688  -0.0927   0.9150   0.0262
  -9.500  -0.4169   0.02075   0.01568  -0.0925   0.9065   0.0265
  -9.250  -0.3930   0.01969   0.01442  -0.0922   0.8966   0.0268
  -9.000  -0.3686   0.01867   0.01320  -0.0919   0.8868   0.0270
  -8.500  -0.3183   0.01696   0.01113  -0.0913   0.8654   0.0275
  -8.250  -0.2925   0.01623   0.01023  -0.0910   0.8550   0.0278
  -8.000  -0.2665   0.01558   0.00941  -0.0907   0.8439   0.0281
  -7.750  -0.2401   0.01499   0.00868  -0.0905   0.8320   0.0283
  -7.500  -0.2135   0.01448   0.00803  -0.0902   0.8193   0.0286
  -7.250  -0.1869   0.01403   0.00744  -0.0899   0.8054   0.0288
  -7.000  -0.1600   0.01364   0.00692  -0.0896   0.7904   0.0290
  -6.750  -0.1338   0.01305   0.00623  -0.0893   0.7749   0.0294
  -6.250  -0.0800   0.01239   0.00540  -0.0889   0.7400   0.0304
  -6.000  -0.0530   0.01212   0.00504  -0.0886   0.7199   0.0308
  -5.750  -0.0260   0.01188   0.00468  -0.0884   0.6994   0.0312
  -5.500   0.0011   0.01166   0.00436  -0.0881   0.6811   0.0316
  -5.250   0.0284   0.01146   0.00407  -0.0879   0.6662   0.0321
  -5.000   0.0559   0.01128   0.00379  -0.0878   0.6530   0.0325
  -4.500   0.1113   0.01096   0.00333  -0.0875   0.6301   0.0335
  -4.250   0.1390   0.01080   0.00311  -0.0874   0.6196   0.0341
  -4.000   0.1667   0.01066   0.00290  -0.0873   0.6079   0.0350
  -3.750   0.1946   0.01055   0.00275  -0.0872   0.5964   0.0360
  -3.500   0.2225   0.01047   0.00262  -0.0871   0.5872   0.0374
  -3.250   0.2509   0.01038   0.00250  -0.0871   0.5797   0.0387
  -3.000   0.2789   0.01029   0.00238  -0.0871   0.5730   0.0404
  -2.750   0.3073   0.01020   0.00229  -0.0870   0.5667   0.0430
  -2.500   0.3356   0.01012   0.00221  -0.0870   0.5605   0.0473
  -2.000   0.3922   0.00995   0.00212  -0.0870   0.5489   0.0755
  -1.750   0.4204   0.00988   0.00209  -0.0870   0.5426   0.0935
  -1.500   0.4484   0.00981   0.00208  -0.0870   0.5371   0.1187
  -1.250   0.4767   0.00964   0.00209  -0.0871   0.5318   0.1743
  -0.750   0.5322   0.00930   0.00213  -0.0871   0.5197   0.3197
  -0.500   0.5595   0.00889   0.00221  -0.0872   0.5138   0.4908
  -0.250   0.5844   0.00834   0.00231  -0.0867   0.5080   0.7032
   0.250   0.6438   0.00788   0.00242  -0.0866   0.4955   1.0000
   0.500   0.6713   0.00800   0.00246  -0.0864   0.4881   1.0000
   0.750   0.6990   0.00809   0.00251  -0.0863   0.4789   1.0000
   1.000   0.7261   0.00823   0.00257  -0.0861   0.4657   1.0000
   1.250   0.7530   0.00838   0.00263  -0.0858   0.4494   1.0000
   1.500   0.7800   0.00854   0.00271  -0.0856   0.4344   1.0000
   1.750   0.8068   0.00872   0.00280  -0.0853   0.4192   1.0000
   2.000   0.8336   0.00890   0.00291  -0.0850   0.4041   1.0000
   2.500   0.8867   0.00931   0.00317  -0.0845   0.3754   1.0000
   2.750   0.9130   0.00954   0.00333  -0.0842   0.3610   1.0000
   3.000   0.9392   0.00978   0.00350  -0.0839   0.3474   1.0000
   3.250   0.9653   0.01003   0.00369  -0.0835   0.3352   1.0000
   3.500   0.9912   0.01029   0.00389  -0.0832   0.3243   1.0000
   3.750   1.0175   0.01051   0.00409  -0.0829   0.3144   1.0000
   4.000   1.0434   0.01076   0.00430  -0.0825   0.3050   1.0000
   4.250   1.0686   0.01106   0.00455  -0.0821   0.2924   1.0000
   4.500   1.0935   0.01139   0.00480  -0.0816   0.2765   1.0000
   4.750   1.1182   0.01173   0.00506  -0.0811   0.2598   1.0000
   5.000   1.1428   0.01207   0.00535  -0.0806   0.2442   1.0000
   5.250   1.1668   0.01244   0.00565  -0.0800   0.2268   1.0000
   5.500   1.1903   0.01286   0.00598  -0.0794   0.2086   1.0000
   5.750   1.2130   0.01333   0.00636  -0.0786   0.1904   1.0000
   6.000   1.2354   0.01380   0.00675  -0.0778   0.1753   1.0000
   6.250   1.2581   0.01423   0.00714  -0.0771   0.1646   1.0000
   6.500   1.2803   0.01468   0.00755  -0.0762   0.1553   1.0000
   6.750   1.3024   0.01513   0.00798  -0.0754   0.1461   1.0000
   7.000   1.3244   0.01555   0.00839  -0.0745   0.1389   1.0000
   7.250   1.3455   0.01602   0.00884  -0.0735   0.1310   1.0000
   7.500   1.3668   0.01645   0.00928  -0.0726   0.1245   1.0000
   7.750   1.3865   0.01698   0.00978  -0.0714   0.1164   1.0000
   8.000   1.4061   0.01748   0.01028  -0.0702   0.1074   1.0000
   8.250   1.4228   0.01813   0.01087  -0.0687   0.0936   1.0000
   8.500   1.4265   0.01943   0.01191  -0.0653   0.0600   1.0000
   8.750   1.4366   0.02036   0.01281  -0.0628   0.0516   1.0000
   9.000   1.4481   0.02123   0.01370  -0.0607   0.0470   1.0000
   9.250   1.4612   0.02203   0.01454  -0.0588   0.0442   1.0000
   9.500   1.4734   0.02291   0.01546  -0.0570   0.0418   1.0000
   9.750   1.4838   0.02394   0.01653  -0.0552   0.0397   1.0000
  10.000   1.4960   0.02489   0.01754  -0.0536   0.0383   1.0000
  10.250   1.5074   0.02593   0.01864  -0.0520   0.0368   1.0000
  10.500   1.5172   0.02713   0.01989  -0.0505   0.0354   1.0000
  10.750   1.5253   0.02851   0.02133  -0.0490   0.0342   1.0000
  11.000   1.5331   0.02998   0.02287  -0.0476   0.0331   1.0000
  11.250   1.5424   0.03138   0.02435  -0.0465   0.0322   1.0000
  11.500   1.5504   0.03296   0.02600  -0.0454   0.0312   1.0000
  11.750   1.5567   0.03474   0.02785  -0.0445   0.0303   1.0000
  12.000   1.5614   0.03675   0.02993  -0.0436   0.0294   1.0000
  12.250   1.5639   0.03905   0.03231  -0.0428   0.0286   1.0000
  12.500   1.5675   0.04134   0.03468  -0.0422   0.0280   1.0000
  12.750   1.5716   0.04362   0.03706  -0.0418   0.0273   1.0000
  13.000   1.5744   0.04612   0.03966  -0.0415   0.0266   1.0000
  13.250   1.5758   0.04882   0.04245  -0.0413   0.0259   1.0000
  13.500   1.5756   0.05177   0.04548  -0.0412   0.0252   1.0000
  13.750   1.5736   0.05499   0.04878  -0.0413   0.0246   1.0000
  14.000   1.5693   0.05858   0.05246  -0.0415   0.0241   1.0000
  14.250   1.5669   0.06199   0.05597  -0.0417   0.0236   1.0000
  14.500   1.5644   0.06544   0.05954  -0.0421   0.0231   1.0000
  14.750   1.5609   0.06909   0.06329  -0.0425   0.0226   1.0000
  15.000   1.5565   0.07294   0.06724  -0.0431   0.0221   1.0000
  15.250   1.5510   0.07697   0.07138  -0.0439   0.0216   1.0000
  15.500   1.5444   0.08123   0.07573  -0.0447   0.0212   1.0000
  15.750   1.5366   0.08574   0.08034  -0.0458   0.0207   1.0000
  16.000   1.5276   0.09054   0.08522  -0.0470   0.0204   1.0000
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