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USA 29 AIRFOIL (usa29-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: USA 29 AIRFOIL (usa29-il)
Reynolds number: 50,000
Max Cl/Cd: 27.06 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa29-il-50000-n5.txt
Download as CSV file: xf-usa29-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 29 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.2953   0.12809   0.12128  -0.0411   1.0000   0.1356
 -10.250  -0.3116   0.12713   0.12044  -0.0407   1.0000   0.1369
 -10.000  -0.3244   0.12557   0.11897  -0.0400   1.0000   0.1372
  -9.750  -0.3339   0.12357   0.11705  -0.0389   1.0000   0.1373
  -9.250  -0.3544   0.11166   0.10521  -0.0398   1.0000   0.0910
  -9.000  -0.3599   0.10940   0.10300  -0.0381   1.0000   0.0903
  -8.750  -0.3723   0.10719   0.10089  -0.0368   1.0000   0.0903
  -8.500  -0.3742   0.10302   0.09671  -0.0408   0.9945   0.0910
  -8.250  -0.3718   0.09824   0.09193  -0.0464   0.9857   0.0913
  -8.000  -0.3675   0.09380   0.08747  -0.0505   0.9764   0.0912
  -7.750  -0.3575   0.08939   0.08301  -0.0543   0.9676   0.0907
  -7.500  -0.3464   0.08431   0.07786  -0.0594   0.9588   0.0904
  -7.250  -0.3400   0.07936   0.07285  -0.0633   0.9476   0.0903
  -7.000  -0.3410   0.07277   0.06611  -0.0685   0.9355   0.0913
  -6.750  -0.3260   0.06890   0.06215  -0.0713   0.9269   0.0930
  -6.500  -0.3130   0.06521   0.05833  -0.0732   0.9168   0.0941
  -6.250  -0.3105   0.05885   0.05165  -0.0758   0.9053   0.0939
  -6.000  -0.2971   0.05362   0.04603  -0.0783   0.8970   0.0944
  -5.750  -0.2860   0.04994   0.04200  -0.0785   0.8864   0.0953
  -5.500  -0.2720   0.04708   0.03880  -0.0783   0.8763   0.0971
  -5.250  -0.2486   0.04407   0.03532  -0.0794   0.8692   0.1005
  -5.000  -0.2360   0.04151   0.03221  -0.0781   0.8583   0.1032
  -4.750  -0.2091   0.03880   0.02882  -0.0788   0.8520   0.1054
  -4.500  -0.1902   0.03729   0.02703  -0.0776   0.8418   0.1071
  -4.250  -0.1644   0.03606   0.02563  -0.0775   0.8340   0.1096
  -4.000  -0.1381   0.03493   0.02429  -0.0774   0.8258   0.1134
  -3.750  -0.1128   0.03390   0.02291  -0.0771   0.8175   0.1189
  -3.500  -0.0831   0.03291   0.02176  -0.0774   0.8102   0.1250
  -3.250  -0.0557   0.03216   0.02088  -0.0774   0.8022   0.1316
  -3.000  -0.0245   0.03130   0.01984  -0.0779   0.7948   0.1398
  -2.750   0.0142   0.03054   0.01901  -0.0798   0.7892   0.1543
  -2.500   0.0403   0.03028   0.01877  -0.0796   0.7797   0.1736
  -2.250   0.0837   0.02971   0.01821  -0.0822   0.7754   0.2084
  -2.000   0.1011   0.02984   0.01834  -0.0804   0.7643   0.2316
  -1.750   0.1332   0.02982   0.01835  -0.0806   0.7595   0.2645
  -1.500   0.1430   0.03034   0.01886  -0.0774   0.7480   0.2847
  -1.250   0.1650   0.03061   0.01903  -0.0759   0.7410   0.3117
  -1.000   0.1834   0.03089   0.01919  -0.0741   0.7323   0.3344
  -0.750   0.2170   0.03070   0.01880  -0.0748   0.7268   0.3557
  -0.500   0.2392   0.03080   0.01876  -0.0740   0.7175   0.3705
  -0.250   0.2796   0.03038   0.01811  -0.0760   0.7133   0.3927
   0.000   0.2983   0.03060   0.01827  -0.0748   0.7035   0.4099
   0.250   0.3415   0.03002   0.01761  -0.0774   0.6990   0.4332
   0.500   0.3665   0.03011   0.01766  -0.0774   0.6904   0.4475
   0.750   0.4059   0.02973   0.01723  -0.0794   0.6850   0.4624
   1.000   0.4378   0.02958   0.01708  -0.0803   0.6785   0.4765
   1.250   0.4653   0.02956   0.01709  -0.0805   0.6712   0.4900
   1.500   0.5053   0.02905   0.01662  -0.0824   0.6671   0.5078
   1.750   0.5177   0.02954   0.01721  -0.0802   0.6579   0.5219
   2.000   0.5513   0.02911   0.01694  -0.0810   0.6530   0.5492
   2.500   0.7049   0.02880   0.01743  -0.1010   0.6403   1.0000
   2.750   0.7399   0.02877   0.01726  -0.1020   0.6357   1.0000
   3.000   0.7460   0.02976   0.01824  -0.0987   0.6267   1.0000
   3.250   0.7760   0.02991   0.01830  -0.0989   0.6215   1.0000
   3.500   0.7877   0.03074   0.01911  -0.0965   0.6140   1.0000
   3.750   0.8083   0.03123   0.01955  -0.0953   0.6075   1.0000
   4.000   0.8440   0.03119   0.01946  -0.0963   0.6034   1.0000
   4.250   0.8373   0.03273   0.02104  -0.0913   0.5940   1.0000
   4.500   0.8674   0.03288   0.02116  -0.0915   0.5892   1.0000
   4.750   0.8685   0.03418   0.02248  -0.0877   0.5812   1.0000
   5.000   0.8861   0.03483   0.02316  -0.0862   0.5752   1.0000
   5.250   0.9223   0.03477   0.02309  -0.0872   0.5715   1.0000
   5.500   0.9006   0.03704   0.02543  -0.0805   0.5614   1.0000
   5.750   0.9312   0.03718   0.02559  -0.0807   0.5571   1.0000
   6.000   0.9099   0.03944   0.02791  -0.0742   0.5479   1.0000
   6.250   0.9290   0.04006   0.02857  -0.0729   0.5426   1.0000
   6.500   0.9700   0.03979   0.02835  -0.0744   0.5395   1.0000
   6.750   0.9247   0.04345   0.03206  -0.0659   0.5277   1.0000
   7.000   0.9591   0.04329   0.03196  -0.0662   0.5245   1.0000
   7.250   0.9211   0.04741   0.03612  -0.0601   0.5124   1.0000
   7.500   0.9514   0.04735   0.03616  -0.0598   0.5092   1.0000
   8.000   0.9467   0.05185   0.04080  -0.0549   0.4936   1.0000
   8.500   0.9439   0.05678   0.04589  -0.0510   0.4780   1.0000
   9.000   0.9441   0.06189   0.05117  -0.0480   0.4625   1.0000
   9.500   0.9451   0.06714   0.05662  -0.0455   0.4470   1.0000
  10.000   0.9464   0.07247   0.06215  -0.0433   0.4318   1.0000
  10.500   0.9481   0.07789   0.06779  -0.0414   0.4167   1.0000
  11.000   0.9504   0.08336   0.07348  -0.0398   0.4017   1.0000
  11.500   0.9537   0.08880   0.07920  -0.0384   0.3868   1.0000
  11.750   0.9485   0.09221   0.08272  -0.0379   0.3776   1.0000
  12.000   0.9859   0.08849   0.07921  -0.0352   0.3657   1.0000
  12.250   1.0039   0.08627   0.07715  -0.0324   0.3462   1.0000
  12.500   1.0299   0.08300   0.07411  -0.0296   0.3277   1.0000
  12.750   1.0539   0.08017   0.07147  -0.0270   0.3073   1.0000
  13.000   1.0461   0.08363   0.07508  -0.0266   0.2910   1.0000
  13.250   1.0345   0.08776   0.07933  -0.0266   0.2705   1.0000
  13.500   1.0305   0.09071   0.08240  -0.0262   0.2438   1.0000
  13.750   1.0403   0.08917   0.07944  -0.0230   0.1038   1.0000
  14.000   1.0236   0.09454   0.08449  -0.0235   0.0836   1.0000
  14.250   1.0111   0.09954   0.08933  -0.0241   0.0734   1.0000
  14.500   1.0031   0.10398   0.09373  -0.0246   0.0672   1.0000
  14.750   0.9972   0.10814   0.09787  -0.0251   0.0628   1.0000
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