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USA 29 AIRFOIL (usa29-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: USA 29 AIRFOIL (usa29-il)
Reynolds number: 200,000
Max Cl/Cd: 74.57 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa29-il-200000.txt
Download as CSV file: xf-usa29-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.1607   0.10364   0.10042  -0.0604   0.9797   0.0760
 -10.000  -0.3173   0.10989   0.10663  -0.0507   0.9920   0.0709
  -9.750  -0.2821   0.10757   0.10426  -0.0490   0.9900   0.0734
  -9.500  -0.2634   0.10422   0.10088  -0.0524   0.9866   0.0773
  -9.250  -0.2840   0.09892   0.09564  -0.0679   0.9779   0.0821
  -9.000  -0.2569   0.09417   0.09085  -0.0656   0.9764   0.0838
  -8.750  -0.2261   0.09188   0.08852  -0.0660   0.9738   0.0867
  -8.000  -0.1999   0.07832   0.07496  -0.0844   0.9563   0.0979
  -7.500  -0.1652   0.07274   0.06932  -0.0887   0.9436   0.1049
  -7.250  -0.2275   0.04757   0.04365  -0.1093   0.9253   0.0839
  -7.000  -0.2770   0.03318   0.02787  -0.1058   0.9105   0.0718
  -6.750  -0.2627   0.03110   0.02556  -0.1041   0.9019   0.0727
  -6.500  -0.2314   0.02944   0.02374  -0.1054   0.8976   0.0745
  -6.250  -0.2009   0.02690   0.02078  -0.1065   0.8944   0.0753
  -6.000  -0.1851   0.02533   0.01891  -0.1042   0.8848   0.0759
  -5.750  -0.1526   0.02370   0.01699  -0.1052   0.8805   0.0775
  -5.500  -0.1248   0.02248   0.01550  -0.1050   0.8740   0.0794
  -5.250  -0.0968   0.02127   0.01403  -0.1048   0.8665   0.0805
  -5.000  -0.0592   0.02007   0.01255  -0.1064   0.8625   0.0818
  -4.750  -0.0375   0.01904   0.01139  -0.1049   0.8517   0.0830
  -4.500  -0.0003   0.01795   0.01025  -0.1067   0.8467   0.0860
  -4.250   0.0227   0.01745   0.00971  -0.1055   0.8351   0.0889
  -4.000   0.0517   0.01685   0.00900  -0.1054   0.8257   0.0918
  -3.750   0.0832   0.01628   0.00828  -0.1057   0.8168   0.0949
  -3.500   0.1073   0.01561   0.00763  -0.1048   0.8052   0.0989
  -3.250   0.1351   0.01516   0.00713  -0.1046   0.7951   0.1047
  -3.000   0.1628   0.01467   0.00659  -0.1043   0.7848   0.1136
  -2.750   0.1859   0.01422   0.00618  -0.1032   0.7729   0.1291
  -2.500   0.2114   0.01371   0.00585  -0.1027   0.7624   0.1714
  -2.250   0.2393   0.01346   0.00564  -0.1025   0.7527   0.2182
  -2.000   0.2620   0.01341   0.00563  -0.1014   0.7411   0.2487
  -1.750   0.2864   0.01349   0.00572  -0.1005   0.7311   0.2739
  -1.500   0.3126   0.01363   0.00575  -0.0999   0.7219   0.2957
  -1.250   0.3350   0.01383   0.00588  -0.0986   0.7113   0.3105
  -1.000   0.3604   0.01402   0.00598  -0.0979   0.7027   0.3222
  -0.750   0.3842   0.01419   0.00607  -0.0969   0.6935   0.3331
  -0.500   0.4083   0.01439   0.00617  -0.0959   0.6849   0.3455
  -0.250   0.4330   0.01459   0.00623  -0.0951   0.6767   0.3580
   0.000   0.4573   0.01468   0.00631  -0.0944   0.6684   0.3671
   0.250   0.4831   0.01476   0.00630  -0.0939   0.6609   0.3779
   0.500   0.5071   0.01486   0.00635  -0.0931   0.6532   0.3896
   0.750   0.5328   0.01491   0.00633  -0.0926   0.6458   0.4007
   1.000   0.5589   0.01489   0.00631  -0.0923   0.6386   0.4097
   1.250   0.5846   0.01489   0.00628  -0.0919   0.6314   0.4192
   1.500   0.6120   0.01494   0.00627  -0.0919   0.6251   0.4294
   1.750   0.6364   0.01488   0.00627  -0.0913   0.6177   0.4382
   2.000   0.6655   0.01492   0.00624  -0.0917   0.6118   0.4481
   2.250   0.6888   0.01492   0.00635  -0.0909   0.6049   0.4568
   2.500   0.7155   0.01493   0.00637  -0.0907   0.5986   0.4656
   2.750   0.7422   0.01500   0.00645  -0.0906   0.5928   0.4742
   3.000   0.7648   0.01501   0.00657  -0.0897   0.5862   0.4820
   3.250   0.7921   0.01507   0.00664  -0.0896   0.5808   0.4916
   3.500   0.8147   0.01515   0.00682  -0.0887   0.5748   0.5011
   3.750   0.8377   0.01520   0.00697  -0.0878   0.5686   0.5136
   4.000   0.8660   0.01520   0.00707  -0.0880   0.5637   0.5487
   4.250   1.0187   0.01517   0.00802  -0.1154   0.5531   0.9865
   4.500   1.0818   0.01541   0.00818  -0.1232   0.5471   0.9992
   4.750   1.1035   0.01565   0.00853  -0.1221   0.5409   1.0000
   5.000   1.1257   0.01587   0.00874  -0.1211   0.5354   1.0000
   5.250   1.1514   0.01612   0.00893  -0.1207   0.5307   1.0000
   5.500   1.1681   0.01640   0.00934  -0.1186   0.5248   1.0000
   5.750   1.1900   0.01661   0.00955  -0.1175   0.5192   1.0000
   6.000   1.2093   0.01678   0.00973  -0.1158   0.5118   1.0000
   6.250   1.2264   0.01679   0.00974  -0.1136   0.5020   1.0000
   6.500   1.2400   0.01690   0.00988  -0.1107   0.4920   1.0000
   6.750   1.2602   0.01700   0.00991  -0.1091   0.4837   1.0000
   7.000   1.2704   0.01713   0.01014  -0.1057   0.4737   1.0000
   7.250   1.2844   0.01726   0.01029  -0.1029   0.4641   1.0000
   7.500   1.2976   0.01740   0.01043  -0.1000   0.4542   1.0000
   7.750   1.3054   0.01758   0.01070  -0.0961   0.4428   1.0000
   8.000   1.3110   0.01776   0.01089  -0.0917   0.4293   1.0000
   8.250   1.3141   0.01797   0.01112  -0.0868   0.4152   1.0000
   8.500   1.3107   0.01820   0.01134  -0.0807   0.3992   1.0000
   8.750   1.3044   0.01858   0.01165  -0.0744   0.3778   1.0000
   9.000   1.2948   0.01926   0.01222  -0.0678   0.3457   1.0000
   9.250   1.2785   0.02051   0.01319  -0.0608   0.2934   1.0000
   9.500   1.2594   0.02235   0.01467  -0.0542   0.2372   1.0000
   9.750   1.2315   0.02512   0.01696  -0.0474   0.1680   1.0000
  10.000   1.2020   0.02846   0.01986  -0.0414   0.0982   1.0000
  10.250   1.1814   0.03159   0.02274  -0.0370   0.0587   1.0000
  10.500   1.1745   0.03398   0.02511  -0.0342   0.0500   1.0000
  10.750   1.1720   0.03617   0.02739  -0.0319   0.0457   1.0000
  11.000   1.1713   0.03833   0.02966  -0.0300   0.0435   1.0000
  11.250   1.1672   0.04091   0.03235  -0.0282   0.0415   1.0000
  11.500   1.1604   0.04391   0.03546  -0.0266   0.0400   1.0000
  11.750   1.1535   0.04705   0.03872  -0.0253   0.0386   1.0000
  12.000   1.1515   0.04982   0.04160  -0.0243   0.0379   1.0000
  12.250   1.1479   0.05283   0.04472  -0.0234   0.0366   1.0000
  12.500   1.1440   0.05592   0.04790  -0.0226   0.0357   1.0000
  12.750   1.1402   0.05903   0.05109  -0.0218   0.0351   1.0000
  13.000   1.1374   0.06205   0.05417  -0.0211   0.0343   1.0000
  13.250   1.1349   0.06500   0.05715  -0.0203   0.0336   1.0000
  13.500   1.1344   0.06761   0.05976  -0.0193   0.0328   1.0000
  13.750   1.1383   0.06948   0.06161  -0.0179   0.0321   1.0000
  14.000   1.1499   0.07027   0.06234  -0.0158   0.0314   1.0000
  14.250   1.1588   0.07197   0.06413  -0.0151   0.0307   1.0000
  14.500   1.1690   0.07342   0.06566  -0.0141   0.0297   1.0000
  14.750   1.1842   0.07417   0.06644  -0.0126   0.0292   1.0000
  15.000   1.2010   0.07482   0.06713  -0.0111   0.0286   1.0000
  15.250   1.2200   0.07533   0.06769  -0.0094   0.0280   1.0000
  15.500   1.2396   0.07597   0.06842  -0.0078   0.0279   1.0000
  15.750   1.2592   0.07685   0.06942  -0.0063   0.0277   1.0000
  16.000   1.2751   0.07824   0.07092  -0.0051   0.0274   1.0000
  16.250   1.2962   0.07929   0.07199  -0.0040   0.0267   1.0000
  16.500   1.3112   0.08116   0.07395  -0.0030   0.0263   1.0000
  16.750   1.3196   0.08373   0.07672  -0.0023   0.0264   1.0000
  17.000   1.3084   0.08794   0.08126  -0.0020   0.0268   1.0000
  17.250   1.2914   0.09310   0.08682  -0.0022   0.0278   1.0000
  17.500   1.2845   0.09786   0.09189  -0.0021   0.0292   1.0000
  17.750   1.2794   0.10258   0.09682  -0.0021   0.0302   1.0000
  18.000   1.0433   0.10105   0.09591   0.0054   0.0287   1.0000
  18.250   1.0266   0.10510   0.10018   0.0042   0.0291   1.0000
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