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USA 26 AIRFOIL (usa26-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: USA 26 AIRFOIL (usa26-il)
Reynolds number: 50,000
Max Cl/Cd: 35.29 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa26-il-50000-n5.txt
Download as CSV file: xf-usa26-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 26 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3631   0.09793   0.09157  -0.0233   1.0000   0.1476
  -7.250  -0.3889   0.09744   0.09124  -0.0231   1.0000   0.1511
  -7.000  -0.4008   0.09519   0.08909  -0.0233   1.0000   0.1528
  -6.750  -0.3881   0.09107   0.08500  -0.0199   1.0000   0.1562
  -6.500  -0.3891   0.08853   0.08252  -0.0184   1.0000   0.1599
  -6.000  -0.4072   0.08443   0.07849  -0.0199   1.0000   0.1685
  -5.500  -0.3948   0.07126   0.06490  -0.0264   1.0000   0.0942
  -5.250  -0.3888   0.06830   0.06192  -0.0250   1.0000   0.0929
  -5.000  -0.3819   0.06516   0.05874  -0.0241   1.0000   0.0906
  -4.750  -0.3687   0.05897   0.05203  -0.0271   1.0000   0.0809
  -4.500  -0.3586   0.05621   0.04922  -0.0260   1.0000   0.0798
  -4.250  -0.3321   0.05248   0.04524  -0.0284   0.9949   0.0783
  -4.000  -0.2981   0.04832   0.04063  -0.0322   0.9869   0.0787
  -3.750  -0.2641   0.04449   0.03621  -0.0353   0.9786   0.0799
  -3.500  -0.2303   0.04135   0.03260  -0.0377   0.9701   0.0793
  -3.250  -0.1934   0.03850   0.02923  -0.0403   0.9618   0.0789
  -3.000  -0.1593   0.03613   0.02637  -0.0419   0.9516   0.0789
  -2.750  -0.1241   0.03409   0.02382  -0.0434   0.9410   0.0792
  -2.500  -0.0852   0.03244   0.02156  -0.0453   0.9304   0.0814
  -2.250  -0.0463   0.03087   0.01991  -0.0476   0.9194   0.0850
  -2.000  -0.0101   0.02960   0.01837  -0.0489   0.9062   0.0870
  -1.750   0.0283   0.02840   0.01691  -0.0504   0.8928   0.0888
  -1.500   0.0704   0.02734   0.01560  -0.0525   0.8796   0.0912
  -1.250   0.1124   0.02642   0.01442  -0.0544   0.8658   0.0943
  -1.000   0.1518   0.02551   0.01351  -0.0561   0.8515   0.0992
  -0.750   0.1896   0.02472   0.01270  -0.0573   0.8364   0.1104
  -0.500   0.2263   0.02392   0.01199  -0.0584   0.8206   0.1258
  -0.250   0.2624   0.02308   0.01138  -0.0593   0.8039   0.1607
   0.000   0.2972   0.02222   0.01102  -0.0600   0.7863   0.3073
   0.500   0.4426   0.01990   0.00992  -0.0763   0.7433   1.0000
   0.750   0.4759   0.01982   0.00952  -0.0767   0.7179   1.0000
   1.000   0.5093   0.01979   0.00917  -0.0772   0.6937   1.0000
   1.250   0.5375   0.01990   0.00901  -0.0768   0.6692   1.0000
   1.500   0.5673   0.02004   0.00885  -0.0767   0.6479   1.0000
   1.750   0.5932   0.02028   0.00886  -0.0761   0.6274   1.0000
   2.000   0.6193   0.02056   0.00891  -0.0755   0.6097   1.0000
   2.250   0.6450   0.02088   0.00904  -0.0749   0.5938   1.0000
   2.500   0.6704   0.02123   0.00921  -0.0744   0.5793   1.0000
   2.750   0.6960   0.02161   0.00943  -0.0738   0.5666   1.0000
   3.000   0.7225   0.02200   0.00969  -0.0735   0.5553   1.0000
   3.250   0.7470   0.02244   0.01007  -0.0729   0.5442   1.0000
   3.500   0.7719   0.02290   0.01047  -0.0724   0.5341   1.0000
   3.750   0.7992   0.02334   0.01084  -0.0723   0.5253   1.0000
   4.000   0.8216   0.02387   0.01139  -0.0714   0.5159   1.0000
   4.250   0.8482   0.02436   0.01183  -0.0712   0.5085   1.0000
   4.500   0.8699   0.02494   0.01251  -0.0703   0.5003   1.0000
   4.750   0.8967   0.02546   0.01298  -0.0701   0.4937   1.0000
   5.000   0.9161   0.02610   0.01376  -0.0687   0.4857   1.0000
   5.250   0.9413   0.02667   0.01434  -0.0683   0.4794   1.0000
   5.500   0.9609   0.02738   0.01521  -0.0671   0.4725   1.0000
   5.750   0.9834   0.02798   0.01587  -0.0662   0.4653   1.0000
   6.000   1.0020   0.02863   0.01663  -0.0647   0.4568   1.0000
   6.250   1.0249   0.02909   0.01713  -0.0637   0.4479   1.0000
   6.500   1.0395   0.02971   0.01790  -0.0615   0.4373   1.0000
   6.750   1.0583   0.03021   0.01847  -0.0599   0.4276   1.0000
   7.000   1.0779   0.03073   0.01909  -0.0584   0.4187   1.0000
   7.250   1.0938   0.03147   0.02004  -0.0566   0.4106   1.0000
   7.500   1.1150   0.03198   0.02065  -0.0554   0.4027   1.0000
   7.750   1.1283   0.03280   0.02168  -0.0532   0.3940   1.0000
   8.000   1.1514   0.03325   0.02221  -0.0523   0.3864   1.0000
   8.250   1.1612   0.03419   0.02343  -0.0496   0.3772   1.0000
   8.500   1.1811   0.03474   0.02412  -0.0482   0.3690   1.0000
   8.750   1.1925   0.03563   0.02526  -0.0458   0.3599   1.0000
   9.000   1.2069   0.03641   0.02624  -0.0438   0.3511   1.0000
   9.250   1.2244   0.03661   0.02650  -0.0418   0.3398   1.0000
   9.500   1.2303   0.03700   0.02703  -0.0384   0.3259   1.0000
   9.750   1.2326   0.03747   0.02764  -0.0345   0.3116   1.0000
  10.000   1.2331   0.03818   0.02851  -0.0306   0.2985   1.0000
  10.250   1.2337   0.03905   0.02961  -0.0268   0.2877   1.0000
  10.500   1.2366   0.03980   0.03048  -0.0234   0.2774   1.0000
  10.750   1.2337   0.04083   0.03167  -0.0196   0.2658   1.0000
  11.000   1.2265   0.04236   0.03341  -0.0160   0.2536   1.0000
  11.250   1.2200   0.04409   0.03532  -0.0130   0.2419   1.0000
  11.500   1.2164   0.04593   0.03733  -0.0107   0.2322   1.0000
  11.750   1.2091   0.04810   0.03963  -0.0086   0.2198   1.0000
  12.000   1.1973   0.05086   0.04247  -0.0070   0.2043   1.0000
  12.250   1.1846   0.05400   0.04556  -0.0061   0.1865   1.0000
  12.500   1.1716   0.05760   0.04904  -0.0057   0.1699   1.0000
  12.750   1.1556   0.06200   0.05334  -0.0061   0.1537   1.0000
  13.000   1.1425   0.06668   0.05813  -0.0069   0.1422   1.0000
  13.250   1.1280   0.07179   0.06332  -0.0082   0.1290   1.0000
  13.500   1.1135   0.07709   0.06872  -0.0096   0.1143   1.0000
  13.750   1.1008   0.08225   0.07397  -0.0110   0.0997   1.0000
  14.000   1.0876   0.08754   0.07924  -0.0125   0.0817   1.0000
  14.250   1.0749   0.09271   0.08429  -0.0141   0.0707   1.0000
  14.500   1.0611   0.09820   0.08960  -0.0158   0.0632   1.0000
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