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USA-35B AIRFOIL (usa35b-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: USA-35B AIRFOIL (usa35b-il)
Reynolds number: 500,000
Max Cl/Cd: 106.04 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa35b-il-500000.txt
Download as CSV file: xf-usa35b-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.3628   0.11786   0.11536  -0.0251   1.0000   0.0316
 -12.250  -0.3577   0.11453   0.11204  -0.0266   1.0000   0.0326
 -12.000  -0.3766   0.10665   0.10418  -0.0354   1.0000   0.0342
 -11.750  -0.3694   0.10338   0.10092  -0.0348   1.0000   0.0345
 -11.500  -0.3599   0.10099   0.09855  -0.0347   1.0000   0.0347
 -11.250  -0.3508   0.09861   0.09619  -0.0349   1.0000   0.0349
 -11.000  -0.3430   0.09609   0.09369  -0.0354   1.0000   0.0353
 -10.750  -0.3370   0.09340   0.09101  -0.0362   1.0000   0.0358
 -10.500  -0.3328   0.09056   0.08819  -0.0372   1.0000   0.0364
 -10.250  -0.2677   0.07226   0.07009  -0.0491   0.9943   0.0400
 -10.000  -0.2517   0.06915   0.06699  -0.0508   0.9913   0.0403
  -9.750  -0.2365   0.06580   0.06364  -0.0532   0.9875   0.0408
  -9.500  -0.2233   0.06190   0.05974  -0.0566   0.9832   0.0414
  -9.250  -0.2156   0.05760   0.05544  -0.0602   0.9744   0.0422
  -9.000  -0.2571   0.03532   0.03273  -0.0883   0.9560   0.0460
  -8.750  -0.2419   0.03335   0.03079  -0.0878   0.9457   0.0464
  -8.500  -0.2265   0.03134   0.02876  -0.0877   0.9359   0.0468
  -8.250  -0.2115   0.02931   0.02666  -0.0876   0.9251   0.0472
  -8.000  -0.1963   0.02708   0.02435  -0.0878   0.9133   0.0480
  -7.750  -0.2189   0.02295   0.01812  -0.0951   0.9244   0.0399
  -7.500  -0.1953   0.02148   0.01651  -0.0944   0.9138   0.0392
  -7.250  -0.1725   0.01931   0.01406  -0.0939   0.9042   0.0389
  -7.000  -0.1481   0.01790   0.01238  -0.0933   0.8935   0.0390
  -6.750  -0.1224   0.01700   0.01124  -0.0928   0.8826   0.0393
  -6.500  -0.0965   0.01605   0.01008  -0.0923   0.8717   0.0395
  -6.250  -0.0704   0.01510   0.00895  -0.0918   0.8591   0.0396
  -6.000  -0.0446   0.01393   0.00763  -0.0914   0.8455   0.0399
  -5.750  -0.0184   0.01308   0.00669  -0.0909   0.8313   0.0404
  -5.500   0.0082   0.01250   0.00603  -0.0905   0.8162   0.0409
  -5.250   0.0350   0.01206   0.00551  -0.0901   0.7995   0.0415
  -5.000   0.0618   0.01169   0.00506  -0.0897   0.7809   0.0422
  -4.750   0.0888   0.01141   0.00468  -0.0893   0.7610   0.0433
  -4.500   0.1157   0.01117   0.00432  -0.0890   0.7409   0.0444
  -4.250   0.1427   0.01095   0.00398  -0.0886   0.7200   0.0452
  -4.000   0.1696   0.01068   0.00359  -0.0882   0.6990   0.0461
  -3.750   0.1963   0.01039   0.00323  -0.0879   0.6804   0.0477
  -3.500   0.2238   0.01026   0.00303  -0.0877   0.6655   0.0494
  -3.250   0.2515   0.01016   0.00285  -0.0875   0.6538   0.0517
  -3.000   0.2793   0.01000   0.00265  -0.0874   0.6431   0.0550
  -2.750   0.3074   0.00992   0.00254  -0.0873   0.6339   0.0605
  -2.500   0.3353   0.00975   0.00240  -0.0872   0.6254   0.0750
  -2.250   0.3633   0.00954   0.00230  -0.0872   0.6176   0.1119
  -2.000   0.3910   0.00930   0.00228  -0.0872   0.6098   0.1869
  -1.750   0.4186   0.00908   0.00227  -0.0872   0.6030   0.2658
  -1.500   0.4454   0.00855   0.00232  -0.0873   0.5962   0.4554
  -1.250   0.4708   0.00809   0.00239  -0.0869   0.5897   0.6416
  -1.000   0.4880   0.00743   0.00252  -0.0839   0.5837   0.9024
  -0.750   0.5335   0.00741   0.00248  -0.0874   0.5763   1.0000
  -0.500   0.5608   0.00754   0.00251  -0.0872   0.5705   1.0000
  -0.250   0.5886   0.00760   0.00254  -0.0870   0.5641   1.0000
   0.000   0.6161   0.00771   0.00257  -0.0868   0.5575   1.0000
   0.250   0.6437   0.00781   0.00262  -0.0866   0.5512   1.0000
   0.500   0.6715   0.00789   0.00267  -0.0865   0.5446   1.0000
   1.000   0.7264   0.00809   0.00276  -0.0861   0.5274   1.0000
   1.250   0.7536   0.00820   0.00281  -0.0858   0.5171   1.0000
   1.500   0.7810   0.00831   0.00287  -0.0856   0.5073   1.0000
   1.750   0.8084   0.00841   0.00294  -0.0854   0.4976   1.0000
   2.000   0.8355   0.00855   0.00302  -0.0852   0.4880   1.0000
   2.250   0.8630   0.00865   0.00311  -0.0850   0.4780   1.0000
   2.500   0.8901   0.00879   0.00321  -0.0848   0.4682   1.0000
   2.750   0.9171   0.00893   0.00332  -0.0846   0.4571   1.0000
   3.000   0.9442   0.00907   0.00344  -0.0844   0.4453   1.0000
   3.250   0.9709   0.00924   0.00357  -0.0841   0.4328   1.0000
   3.500   0.9972   0.00944   0.00372  -0.0838   0.4191   1.0000
   3.750   1.0233   0.00965   0.00388  -0.0834   0.4046   1.0000
   4.000   1.0491   0.00990   0.00407  -0.0830   0.3896   1.0000
   4.250   1.0745   0.01017   0.00428  -0.0826   0.3727   1.0000
   4.500   1.0995   0.01048   0.00451  -0.0821   0.3554   1.0000
   4.750   1.1243   0.01080   0.00476  -0.0816   0.3394   1.0000
   5.000   1.1489   0.01113   0.00504  -0.0810   0.3248   1.0000
   5.250   1.1734   0.01147   0.00532  -0.0805   0.3117   1.0000
   5.500   1.1983   0.01177   0.00560  -0.0800   0.2986   1.0000
   5.750   1.2224   0.01212   0.00591  -0.0794   0.2831   1.0000
   6.000   1.2462   0.01250   0.00623  -0.0788   0.2670   1.0000
   6.250   1.2695   0.01289   0.00656  -0.0781   0.2507   1.0000
   6.500   1.2921   0.01334   0.00694  -0.0773   0.2330   1.0000
   6.750   1.3141   0.01381   0.00734  -0.0765   0.2139   1.0000
   7.000   1.3352   0.01434   0.00779  -0.0755   0.1959   1.0000
   7.250   1.3556   0.01490   0.00828  -0.0744   0.1804   1.0000
   7.500   1.3759   0.01544   0.00878  -0.0733   0.1684   1.0000
   7.750   1.3956   0.01600   0.00930  -0.0722   0.1578   1.0000
   8.000   1.4145   0.01658   0.00984  -0.0709   0.1474   1.0000
   8.250   1.4338   0.01711   0.01036  -0.0696   0.1368   1.0000
   8.500   1.4504   0.01779   0.01098  -0.0681   0.1226   1.0000
   8.750   1.4628   0.01859   0.01169  -0.0658   0.1026   1.0000
   9.000   1.4636   0.02006   0.01286  -0.0621   0.0653   1.0000
   9.250   1.4687   0.02134   0.01407  -0.0591   0.0553   1.0000
   9.500   1.4763   0.02250   0.01525  -0.0567   0.0510   1.0000
   9.750   1.4838   0.02372   0.01652  -0.0544   0.0480   1.0000
  10.000   1.4936   0.02483   0.01771  -0.0525   0.0459   1.0000
  10.250   1.5003   0.02621   0.01915  -0.0506   0.0440   1.0000
  10.500   1.5017   0.02808   0.02107  -0.0484   0.0421   1.0000
  10.750   1.5100   0.02951   0.02258  -0.0470   0.0408   1.0000
  11.000   1.5172   0.03108   0.02425  -0.0457   0.0395   1.0000
  11.250   1.5223   0.03291   0.02615  -0.0444   0.0383   1.0000
  11.500   1.5244   0.03511   0.02842  -0.0433   0.0372   1.0000
  11.750   1.5209   0.03796   0.03135  -0.0422   0.0362   1.0000
  12.000   1.5195   0.04074   0.03423  -0.0415   0.0353   1.0000
  12.250   1.5244   0.04296   0.03656  -0.0410   0.0345   1.0000
  12.500   1.5265   0.04553   0.03922  -0.0406   0.0336   1.0000
  12.750   1.5270   0.04835   0.04213  -0.0404   0.0327   1.0000
  13.000   1.5256   0.05143   0.04529  -0.0403   0.0320   1.0000
  13.250   1.5213   0.05492   0.04886  -0.0403   0.0314   1.0000
  13.500   1.5125   0.05901   0.05302  -0.0405   0.0308   1.0000
  13.750   1.5032   0.06318   0.05727  -0.0406   0.0302   1.0000
  14.000   1.5033   0.06635   0.06056  -0.0409   0.0297   1.0000
  14.250   1.5018   0.06977   0.06409  -0.0413   0.0291   1.0000
  14.500   1.4991   0.07339   0.06781  -0.0418   0.0285   1.0000
  14.750   1.4956   0.07713   0.07164  -0.0424   0.0280   1.0000
  15.000   1.4918   0.08098   0.07557  -0.0432   0.0274   1.0000
  15.250   1.4873   0.08497   0.07963  -0.0440   0.0269   1.0000
  15.500   1.4817   0.08914   0.08385  -0.0449   0.0264   1.0000
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