Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

SD7034 (sd7034-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: SD7034 (sd7034-il)
Reynolds number: 1,000,000
Max Cl/Cd: 128.44 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd7034-il-1000000.txt
Download as CSV file: xf-sd7034-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD7034                                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.2592   0.10071   0.09922  -0.0294   0.9672   0.0140
 -10.250  -0.6266   0.03512   0.03310  -0.0795   0.9649   0.0089
 -10.000  -0.6350   0.02864   0.02604  -0.0822   0.9339   0.0090
  -9.750  -0.6267   0.02553   0.02255  -0.0822   0.9189   0.0090
  -9.500  -0.6109   0.02345   0.02017  -0.0819   0.9081   0.0091
  -9.000  -0.5784   0.01846   0.01445  -0.0814   0.8887   0.0097
  -8.750  -0.5547   0.01768   0.01356  -0.0811   0.8810   0.0099
  -8.500  -0.5292   0.01715   0.01295  -0.0809   0.8731   0.0102
  -8.250  -0.5044   0.01645   0.01211  -0.0806   0.8659   0.0106
  -8.000  -0.4788   0.01569   0.01121  -0.0805   0.8582   0.0110
  -7.750  -0.4535   0.01497   0.01032  -0.0802   0.8512   0.0113
  -7.500  -0.4271   0.01431   0.00953  -0.0800   0.8438   0.0117
  -7.250  -0.4004   0.01388   0.00895  -0.0798   0.8368   0.0119
  -7.000  -0.3756   0.01261   0.00753  -0.0796   0.8297   0.0126
  -6.750  -0.3486   0.01219   0.00705  -0.0795   0.8225   0.0131
  -6.500  -0.3211   0.01182   0.00661  -0.0794   0.8156   0.0137
  -6.250  -0.2937   0.01145   0.00614  -0.0793   0.8083   0.0144
  -6.000  -0.2658   0.01119   0.00579  -0.0791   0.8015   0.0150
  -5.750  -0.2390   0.01049   0.00502  -0.0790   0.7940   0.0161
  -5.500  -0.2113   0.01026   0.00473  -0.0789   0.7871   0.0171
  -5.250  -0.1831   0.01005   0.00447  -0.0789   0.7796   0.0183
  -5.000  -0.1556   0.00961   0.00395  -0.0788   0.7726   0.0197
  -4.750  -0.1274   0.00935   0.00367  -0.0787   0.7651   0.0212
  -4.500  -0.0993   0.00916   0.00341  -0.0786   0.7580   0.0226
  -4.250  -0.0712   0.00881   0.00302  -0.0786   0.7506   0.0245
  -4.000  -0.0430   0.00864   0.00281  -0.0786   0.7432   0.0267
  -3.750  -0.0146   0.00844   0.00256  -0.0786   0.7358   0.0289
  -3.500   0.0136   0.00823   0.00233  -0.0785   0.7281   0.0323
  -3.250   0.0421   0.00804   0.00213  -0.0785   0.7205   0.0368
  -3.000   0.0705   0.00789   0.00195  -0.0785   0.7125   0.0435
  -2.750   0.0990   0.00773   0.00182  -0.0785   0.7046   0.0538
  -2.500   0.1273   0.00763   0.00171  -0.0785   0.6963   0.0629
  -2.250   0.1559   0.00751   0.00160  -0.0785   0.6880   0.0731
  -2.000   0.1842   0.00741   0.00150  -0.0785   0.6795   0.0853
  -1.750   0.2128   0.00729   0.00141  -0.0785   0.6707   0.1010
  -1.500   0.2412   0.00718   0.00133  -0.0786   0.6620   0.1245
  -1.250   0.2695   0.00703   0.00127  -0.0786   0.6528   0.1598
  -1.000   0.2977   0.00685   0.00122  -0.0787   0.6440   0.2139
  -0.750   0.3257   0.00662   0.00118  -0.0788   0.6347   0.2937
  -0.500   0.3538   0.00639   0.00117  -0.0789   0.6253   0.3750
  -0.250   0.3817   0.00622   0.00117  -0.0789   0.6159   0.4534
   0.000   0.4095   0.00605   0.00118  -0.0789   0.6059   0.5364
   0.250   0.4371   0.00587   0.00121  -0.0789   0.5961   0.6231
   0.500   0.4642   0.00573   0.00125  -0.0786   0.5858   0.7053
   0.750   0.4900   0.00552   0.00130  -0.0780   0.5752   0.8040
   1.000   0.5115   0.00525   0.00134  -0.0762   0.5651   0.9379
   1.250   0.5504   0.00529   0.00133  -0.0785   0.5536   1.0000
   1.500   0.5784   0.00539   0.00136  -0.0784   0.5421   1.0000
   1.750   0.6065   0.00548   0.00139  -0.0784   0.5307   1.0000
   2.000   0.6346   0.00559   0.00144  -0.0784   0.5193   1.0000
   2.250   0.6625   0.00571   0.00149  -0.0783   0.5075   1.0000
   2.500   0.6903   0.00585   0.00155  -0.0783   0.4952   1.0000
   2.750   0.7182   0.00597   0.00162  -0.0783   0.4826   1.0000
   3.000   0.7460   0.00610   0.00170  -0.0782   0.4699   1.0000
   3.250   0.7737   0.00624   0.00178  -0.0782   0.4570   1.0000
   3.500   0.8013   0.00640   0.00187  -0.0781   0.4437   1.0000
   3.750   0.8288   0.00656   0.00198  -0.0781   0.4305   1.0000
   4.000   0.8562   0.00673   0.00209  -0.0780   0.4167   1.0000
   4.250   0.8834   0.00692   0.00222  -0.0779   0.4028   1.0000
   4.500   0.9105   0.00711   0.00235  -0.0778   0.3885   1.0000
   5.000   0.9646   0.00751   0.00264  -0.0776   0.3600   1.0000
   5.250   0.9914   0.00772   0.00280  -0.0775   0.3457   1.0000
   5.500   1.0180   0.00795   0.00298  -0.0774   0.3311   1.0000
   5.750   1.0444   0.00820   0.00316  -0.0772   0.3163   1.0000
   6.000   1.0706   0.00846   0.00336  -0.0770   0.3010   1.0000
   6.250   1.0966   0.00873   0.00358  -0.0768   0.2857   1.0000
   6.500   1.1224   0.00901   0.00380  -0.0766   0.2710   1.0000
   6.750   1.1481   0.00930   0.00403  -0.0763   0.2564   1.0000
   7.000   1.1736   0.00960   0.00428  -0.0760   0.2426   1.0000
   7.250   1.1989   0.00990   0.00453  -0.0757   0.2292   1.0000
   7.500   1.2240   0.01021   0.00480  -0.0754   0.2163   1.0000
   7.750   1.2487   0.01055   0.00510  -0.0751   0.2028   1.0000
   8.000   1.2730   0.01091   0.00540  -0.0747   0.1896   1.0000
   8.250   1.2969   0.01129   0.00573  -0.0742   0.1760   1.0000
   8.500   1.3204   0.01170   0.00608  -0.0737   0.1624   1.0000
   8.750   1.3433   0.01214   0.00647  -0.0731   0.1482   1.0000
   9.000   1.3656   0.01261   0.00687  -0.0724   0.1342   1.0000
   9.250   1.3872   0.01312   0.00731  -0.0717   0.1202   1.0000
   9.500   1.4079   0.01367   0.00779  -0.0708   0.1062   1.0000
   9.750   1.4279   0.01424   0.00830  -0.0698   0.0933   1.0000
  10.000   1.4475   0.01482   0.00883  -0.0688   0.0822   1.0000
  10.250   1.4662   0.01541   0.00938  -0.0677   0.0722   1.0000
  10.500   1.4837   0.01605   0.00998  -0.0663   0.0632   1.0000
  10.750   1.4996   0.01674   0.01063  -0.0648   0.0549   1.0000
  11.000   1.5156   0.01733   0.01122  -0.0633   0.0499   1.0000
  11.250   1.5270   0.01798   0.01187  -0.0609   0.0450   1.0000
  11.500   1.5384   0.01862   0.01254  -0.0587   0.0415   1.0000
  11.750   1.5470   0.01946   0.01337  -0.0563   0.0373   1.0000
  12.000   1.5590   0.02017   0.01413  -0.0544   0.0349   1.0000
  12.250   1.5676   0.02113   0.01510  -0.0524   0.0321   1.0000
  12.500   1.5772   0.02209   0.01610  -0.0506   0.0296   1.0000
  12.750   1.5871   0.02307   0.01713  -0.0490   0.0277   1.0000
  13.000   1.5935   0.02436   0.01844  -0.0472   0.0253   1.0000
  13.250   1.6019   0.02557   0.01970  -0.0457   0.0238   1.0000
  13.500   1.6105   0.02681   0.02100  -0.0444   0.0223   1.0000
  13.750   1.6155   0.02840   0.02262  -0.0430   0.0206   1.0000
  14.000   1.6194   0.03017   0.02445  -0.0417   0.0194   1.0000
  14.250   1.6270   0.03168   0.02603  -0.0408   0.0185   1.0000
  14.500   1.6321   0.03346   0.02787  -0.0399   0.0175   1.0000
  14.750   1.6339   0.03564   0.03010  -0.0390   0.0164   1.0000
  15.000   1.6317   0.03831   0.03285  -0.0383   0.0155   1.0000
  15.250   1.6361   0.04040   0.03503  -0.0378   0.0151   1.0000
  15.500   1.6396   0.04265   0.03736  -0.0375   0.0144   1.0000
  15.750   1.6397   0.04533   0.04013  -0.0373   0.0138   1.0000
  16.000   1.6380   0.04837   0.04324  -0.0374   0.0132   1.0000
  16.250   1.6332   0.05192   0.04688  -0.0376   0.0127   1.0000
  16.500   1.6232   0.05631   0.05138  -0.0383   0.0122   1.0000
  16.750   1.6228   0.05959   0.05476  -0.0389   0.0119   1.0000
  17.000   1.6205   0.06322   0.05849  -0.0398   0.0116   1.0000
  17.250   1.6153   0.06737   0.06275  -0.0409   0.0113   1.0000
  17.500   1.6107   0.07156   0.06704  -0.0421   0.0110   1.0000
  17.750   1.6023   0.07645   0.07203  -0.0438   0.0107   1.0000
  18.000   1.5934   0.08153   0.07722  -0.0456   0.0105   1.0000
  18.250   1.5827   0.08706   0.08286  -0.0478   0.0102   1.0000
  18.500   1.5700   0.09311   0.08901  -0.0503   0.0100   1.0000
  18.750   1.5539   0.09982   0.09584  -0.0533   0.0098   1.0000
  19.000   1.5352   0.10724   0.10340  -0.0568   0.0096   1.0000
<< Back to SD7034 (sd7034-il)

Polar data table (+)

Polar graphs


<< Back to SD7034 (sd7034-il)