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USA 26 AIRFOIL (usa26-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: USA 26 AIRFOIL (usa26-il)
Reynolds number: 200,000
Max Cl/Cd: 69.14 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa26-il-200000-n5.txt
Download as CSV file: xf-usa26-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3545   0.10327   0.09974  -0.0299   1.0000   0.0239
  -9.250  -0.3594   0.10004   0.09655  -0.0300   1.0000   0.0241
  -9.000  -0.3652   0.09693   0.09348  -0.0299   1.0000   0.0242
  -8.500  -0.3703   0.09276   0.08941  -0.0280   1.0000   0.0265
  -8.250  -0.3729   0.09109   0.08780  -0.0267   1.0000   0.0276
  -8.000  -0.3827   0.08894   0.08570  -0.0254   1.0000   0.0282
  -7.750  -0.3756   0.08421   0.08098  -0.0309   0.9954   0.0280
  -7.500  -0.3645   0.07902   0.07577  -0.0374   0.9891   0.0281
  -7.250  -0.3479   0.07318   0.06988  -0.0448   0.9832   0.0282
  -7.000  -0.3309   0.06788   0.06450  -0.0511   0.9767   0.0299
  -6.750  -0.3151   0.06155   0.05805  -0.0574   0.9695   0.0308
  -6.500  -0.2949   0.05453   0.05084  -0.0635   0.9636   0.0312
  -6.000  -0.2614   0.04024   0.03586  -0.0705   0.9500   0.0336
  -5.750  -0.2434   0.03767   0.03312  -0.0704   0.9425   0.0342
  -5.500  -0.2193   0.03394   0.02904  -0.0716   0.9365   0.0347
  -5.250  -0.1973   0.03114   0.02593  -0.0716   0.9285   0.0354
  -5.000  -0.1693   0.02899   0.02350  -0.0724   0.9213   0.0369
  -4.750  -0.1478   0.02669   0.02083  -0.0715   0.9124   0.0377
  -4.500  -0.1211   0.02446   0.01819  -0.0715   0.9059   0.0381
  -4.250  -0.0986   0.02283   0.01624  -0.0704   0.8972   0.0386
  -4.000  -0.0688   0.02129   0.01438  -0.0708   0.8908   0.0391
  -3.750  -0.0434   0.02018   0.01301  -0.0701   0.8814   0.0398
  -3.500  -0.0079   0.01920   0.01175  -0.0715   0.8748   0.0411
  -3.250   0.0197   0.01830   0.01064  -0.0712   0.8641   0.0416
  -3.000   0.0518   0.01738   0.00953  -0.0718   0.8536   0.0418
  -2.750   0.0868   0.01655   0.00852  -0.0731   0.8422   0.0422
  -2.500   0.1223   0.01555   0.00738  -0.0744   0.8278   0.0429
  -2.250   0.1570   0.01468   0.00643  -0.0757   0.8102   0.0439
  -2.000   0.1906   0.01409   0.00576  -0.0767   0.7894   0.0448
  -1.750   0.2213   0.01365   0.00523  -0.0771   0.7651   0.0459
  -1.500   0.2499   0.01338   0.00485  -0.0770   0.7358   0.0480
  -1.250   0.2760   0.01320   0.00450  -0.0764   0.6998   0.0501
  -1.000   0.2996   0.01309   0.00419  -0.0753   0.6588   0.0516
  -0.750   0.3210   0.01307   0.00392  -0.0737   0.6170   0.0529
  -0.500   0.3421   0.01310   0.00373  -0.0722   0.5834   0.0543
  -0.250   0.3633   0.01305   0.00352  -0.0707   0.5592   0.0569
   0.000   0.3854   0.01305   0.00338  -0.0694   0.5405   0.0612
   0.250   0.4082   0.01307   0.00326  -0.0683   0.5249   0.0674
   0.500   0.4308   0.01298   0.00316  -0.0671   0.5112   0.0830
   0.750   0.4503   0.01260   0.00327  -0.0656   0.4992   0.2350
   1.000   0.4725   0.01259   0.00335  -0.0645   0.4877   0.2937
   1.250   0.4946   0.01260   0.00341  -0.0633   0.4769   0.3401
   1.500   0.5157   0.01244   0.00343  -0.0620   0.4662   0.4124
   2.000   0.6924   0.01206   0.00410  -0.0881   0.4370   1.0000
   2.250   0.7140   0.01223   0.00418  -0.0868   0.4296   1.0000
   2.500   0.7359   0.01238   0.00428  -0.0856   0.4221   1.0000
   2.750   0.7573   0.01257   0.00439  -0.0843   0.4158   1.0000
   3.000   0.7793   0.01272   0.00452  -0.0831   0.4090   1.0000
   3.250   0.8005   0.01292   0.00464  -0.0817   0.4024   1.0000
   3.500   0.8221   0.01308   0.00479  -0.0805   0.3950   1.0000
   3.750   0.8430   0.01328   0.00493  -0.0791   0.3878   1.0000
   4.000   0.8644   0.01346   0.00510  -0.0778   0.3808   1.0000
   4.250   0.8854   0.01366   0.00528  -0.0765   0.3742   1.0000
   4.500   0.9065   0.01387   0.00547  -0.0751   0.3690   1.0000
   4.750   0.9283   0.01406   0.00567  -0.0739   0.3637   1.0000
   5.000   0.9492   0.01427   0.00589  -0.0726   0.3584   1.0000
   5.250   0.9702   0.01450   0.00612  -0.0713   0.3533   1.0000
   5.500   0.9917   0.01470   0.00636  -0.0701   0.3481   1.0000
   5.750   1.0124   0.01493   0.00660  -0.0687   0.3431   1.0000
   6.000   1.0331   0.01516   0.00687  -0.0673   0.3377   1.0000
   6.250   1.0533   0.01537   0.00712  -0.0659   0.3305   1.0000
   6.500   1.0722   0.01561   0.00737  -0.0642   0.3223   1.0000
   6.750   1.0912   0.01583   0.00762  -0.0625   0.3130   1.0000
   7.000   1.1099   0.01606   0.00791  -0.0608   0.3034   1.0000
   7.250   1.1270   0.01630   0.00816  -0.0588   0.2897   1.0000
   7.500   1.1443   0.01656   0.00844  -0.0569   0.2766   1.0000
   7.750   1.1613   0.01684   0.00873  -0.0549   0.2596   1.0000
   8.000   1.1759   0.01721   0.00904  -0.0526   0.2342   1.0000
   8.250   1.1863   0.01781   0.00948  -0.0496   0.1966   1.0000
   8.500   1.1930   0.01862   0.01009  -0.0461   0.1682   1.0000
   8.750   1.1996   0.01945   0.01080  -0.0426   0.1456   1.0000
   9.000   1.2051   0.02037   0.01158  -0.0390   0.1187   1.0000
   9.250   1.2073   0.02150   0.01248  -0.0350   0.0761   1.0000
   9.500   1.1940   0.02350   0.01408  -0.0291   0.0260   1.0000
   9.750   1.1982   0.02460   0.01518  -0.0258   0.0213   1.0000
  10.000   1.2062   0.02552   0.01619  -0.0231   0.0196   1.0000
  10.250   1.2131   0.02655   0.01736  -0.0204   0.0182   1.0000
  10.500   1.2182   0.02772   0.01865  -0.0177   0.0170   1.0000
  10.750   1.2220   0.02903   0.02009  -0.0151   0.0161   1.0000
  11.000   1.2220   0.03068   0.02189  -0.0123   0.0152   1.0000
  11.250   1.2247   0.03221   0.02356  -0.0101   0.0148   1.0000
  11.500   1.2272   0.03383   0.02533  -0.0081   0.0146   1.0000
  11.750   1.2267   0.03582   0.02747  -0.0063   0.0142   1.0000
  12.000   1.2248   0.03806   0.02986  -0.0047   0.0139   1.0000
  12.250   1.2218   0.04059   0.03254  -0.0035   0.0137   1.0000
  12.500   1.2176   0.04343   0.03555  -0.0028   0.0134   1.0000
  12.750   1.2111   0.04674   0.03900  -0.0024   0.0131   1.0000
  13.000   1.2059   0.05014   0.04254  -0.0025   0.0129   1.0000
  13.250   1.1989   0.05398   0.04650  -0.0030   0.0125   1.0000
  13.500   1.1917   0.05800   0.05066  -0.0037   0.0124   1.0000
  13.750   1.1844   0.06214   0.05490  -0.0045   0.0121   1.0000
  14.000   1.1768   0.06636   0.05922  -0.0054   0.0119   1.0000
  14.250   1.1697   0.07051   0.06347  -0.0063   0.0118   1.0000
  14.500   1.1616   0.07480   0.06783  -0.0072   0.0115   1.0000
  14.750   1.1558   0.07876   0.07185  -0.0080   0.0113   1.0000
  15.000   1.1510   0.08250   0.07565  -0.0086   0.0111   1.0000
  15.250   1.1483   0.08567   0.07882  -0.0085   0.0108   1.0000
  15.500   1.1493   0.08873   0.08197  -0.0090   0.0107   1.0000
  15.750   1.1503   0.09186   0.08519  -0.0095   0.0106   1.0000
  16.000   1.1526   0.09470   0.08811  -0.0099   0.0105   1.0000
  16.250   1.1546   0.09767   0.09120  -0.0103   0.0104   1.0000
  16.500   1.1555   0.10095   0.09460  -0.0111   0.0102   1.0000
  16.750   1.1575   0.10397   0.09772  -0.0116   0.0101   1.0000
  17.000   1.1580   0.10733   0.10120  -0.0125   0.0099   1.0000
  17.250   1.1593   0.11056   0.10453  -0.0133   0.0099   1.0000
  17.500   1.1569   0.11464   0.10876  -0.0148   0.0095   1.0000
  17.750   1.1559   0.11848   0.11273  -0.0162   0.0094   1.0000
  18.000   1.1531   0.12275   0.11712  -0.0181   0.0091   1.0000
  18.250   1.1508   0.12691   0.12141  -0.0198   0.0090   1.0000
  18.500   1.1477   0.13130   0.12593  -0.0219   0.0089   1.0000
  18.750   1.1436   0.13600   0.13077  -0.0242   0.0088   1.0000
  19.000   1.1412   0.14034   0.13518  -0.0265   0.0085   1.0000
  19.250   1.1366   0.14530   0.14029  -0.0292   0.0085   1.0000
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