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SD7034 (sd7034-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: SD7034 (sd7034-il)
Reynolds number: 500,000
Max Cl/Cd: 107.41 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd7034-il-500000.txt
Download as CSV file: xf-sd7034-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3362   0.09604   0.09383  -0.0338   1.0000   0.0229
  -9.250  -0.3359   0.09153   0.08936  -0.0366   1.0000   0.0230
  -9.000  -0.3342   0.08788   0.08575  -0.0370   1.0000   0.0234
  -8.750  -0.3251   0.08606   0.08395  -0.0370   1.0000   0.0238
  -8.500  -0.3181   0.08383   0.08176  -0.0375   1.0000   0.0243
  -8.250  -0.3131   0.08065   0.07862  -0.0395   0.9932   0.0247
  -8.000  -0.2923   0.07562   0.07357  -0.0470   0.9733   0.0257
  -7.750  -0.3518   0.04257   0.04012  -0.0795   0.9177   0.0186
  -7.500  -0.3515   0.03740   0.03470  -0.0816   0.9035   0.0180
  -7.250  -0.3645   0.02477   0.02084  -0.0845   0.8896   0.0171
  -7.000  -0.3477   0.02119   0.01664  -0.0841   0.8815   0.0175
  -6.750  -0.3252   0.01912   0.01414  -0.0838   0.8730   0.0181
  -6.500  -0.3008   0.01797   0.01263  -0.0832   0.8660   0.0186
  -6.250  -0.2773   0.01606   0.01051  -0.0830   0.8579   0.0195
  -6.000  -0.2516   0.01564   0.01001  -0.0826   0.8512   0.0207
  -5.750  -0.2247   0.01501   0.00926  -0.0824   0.8432   0.0220
  -5.500  -0.1980   0.01449   0.00852  -0.0820   0.8364   0.0230
  -5.250  -0.1724   0.01323   0.00720  -0.0817   0.8286   0.0245
  -5.000  -0.1456   0.01278   0.00666  -0.0814   0.8216   0.0261
  -4.750  -0.1180   0.01240   0.00618  -0.0812   0.8140   0.0279
  -4.500  -0.0915   0.01171   0.00544  -0.0810   0.8067   0.0303
  -4.250  -0.0638   0.01140   0.00508  -0.0808   0.7993   0.0328
  -4.000  -0.0365   0.01093   0.00452  -0.0805   0.7918   0.0353
  -3.750  -0.0089   0.01063   0.00420  -0.0804   0.7845   0.0390
  -3.500   0.0189   0.01032   0.00382  -0.0802   0.7767   0.0427
  -3.250   0.0467   0.01003   0.00353  -0.0801   0.7694   0.0487
  -3.000   0.0746   0.00972   0.00320  -0.0800   0.7614   0.0570
  -2.750   0.1026   0.00947   0.00294  -0.0799   0.7540   0.0685
  -2.500   0.1306   0.00926   0.00274  -0.0798   0.7457   0.0813
  -2.250   0.1587   0.00909   0.00256  -0.0797   0.7380   0.0951
  -2.000   0.1867   0.00891   0.00240  -0.0796   0.7295   0.1133
  -1.750   0.2148   0.00870   0.00226  -0.0796   0.7213   0.1426
  -1.250   0.2701   0.00809   0.00207  -0.0797   0.7041   0.2869
  -1.000   0.2973   0.00776   0.00201  -0.0796   0.6957   0.3927
  -0.750   0.3246   0.00745   0.00200  -0.0795   0.6863   0.4977
  -0.500   0.3512   0.00718   0.00200  -0.0792   0.6777   0.6017
  -0.250   0.3769   0.00689   0.00201  -0.0786   0.6682   0.7103
   0.000   0.4001   0.00660   0.00204  -0.0772   0.6592   0.8225
   0.250   0.4333   0.00635   0.00197  -0.0777   0.6498   0.9735
   0.500   0.4664   0.00639   0.00193  -0.0787   0.6394   1.0000
   0.750   0.4942   0.00647   0.00192  -0.0786   0.6295   1.0000
   1.000   0.5219   0.00657   0.00192  -0.0784   0.6193   1.0000
   1.250   0.5498   0.00665   0.00193  -0.0784   0.6084   1.0000
   1.500   0.5776   0.00674   0.00195  -0.0783   0.5978   1.0000
   1.750   0.6052   0.00686   0.00198  -0.0781   0.5871   1.0000
   2.000   0.6330   0.00696   0.00202  -0.0780   0.5755   1.0000
   2.250   0.6607   0.00707   0.00208  -0.0779   0.5641   1.0000
   2.500   0.6883   0.00720   0.00214  -0.0778   0.5526   1.0000
   2.750   0.7157   0.00734   0.00221  -0.0777   0.5408   1.0000
   3.000   0.7432   0.00747   0.00229  -0.0776   0.5282   1.0000
   3.250   0.7707   0.00761   0.00238  -0.0775   0.5157   1.0000
   3.500   0.7980   0.00776   0.00248  -0.0774   0.5029   1.0000
   3.750   0.8251   0.00793   0.00260  -0.0772   0.4898   1.0000
   4.000   0.8521   0.00811   0.00273  -0.0771   0.4765   1.0000
   4.250   0.8789   0.00830   0.00286  -0.0769   0.4626   1.0000
   4.500   0.9056   0.00850   0.00301  -0.0767   0.4486   1.0000
   4.750   0.9322   0.00872   0.00318  -0.0765   0.4342   1.0000
   5.000   0.9586   0.00894   0.00335  -0.0763   0.4197   1.0000
   5.250   0.9849   0.00917   0.00354  -0.0761   0.4049   1.0000
   5.500   1.0110   0.00942   0.00375  -0.0758   0.3900   1.0000
   5.750   1.0369   0.00968   0.00396  -0.0756   0.3751   1.0000
   6.000   1.0626   0.00996   0.00420  -0.0753   0.3598   1.0000
   6.250   1.0881   0.01025   0.00445  -0.0750   0.3446   1.0000
   6.500   1.1132   0.01056   0.00471  -0.0746   0.3290   1.0000
   6.750   1.1380   0.01090   0.00500  -0.0743   0.3131   1.0000
   7.000   1.1626   0.01124   0.00530  -0.0739   0.2976   1.0000
   7.250   1.1870   0.01159   0.00561  -0.0734   0.2822   1.0000
   7.500   1.2110   0.01197   0.00595  -0.0730   0.2675   1.0000
   7.750   1.2347   0.01236   0.00630  -0.0725   0.2530   1.0000
   8.000   1.2581   0.01276   0.00667  -0.0719   0.2388   1.0000
   8.500   1.3036   0.01363   0.00747  -0.0707   0.2105   1.0000
   8.750   1.3256   0.01410   0.00791  -0.0700   0.1964   1.0000
   9.000   1.3468   0.01460   0.00838  -0.0692   0.1820   1.0000
   9.500   1.3869   0.01572   0.00941  -0.0672   0.1530   1.0000
   9.750   1.4056   0.01633   0.00998  -0.0661   0.1386   1.0000
  10.000   1.4230   0.01699   0.01060  -0.0648   0.1241   1.0000
  10.250   1.4388   0.01771   0.01128  -0.0633   0.1106   1.0000
  10.500   1.4522   0.01848   0.01200  -0.0615   0.0978   1.0000
  10.750   1.4619   0.01930   0.01278  -0.0590   0.0869   1.0000
  11.250   1.4793   0.02113   0.01460  -0.0544   0.0693   1.0000
  11.500   1.4875   0.02217   0.01565  -0.0523   0.0627   1.0000
  11.750   1.4941   0.02338   0.01686  -0.0503   0.0569   1.0000
  12.000   1.5021   0.02456   0.01809  -0.0485   0.0522   1.0000
  12.250   1.5080   0.02594   0.01949  -0.0468   0.0481   1.0000
  12.500   1.5129   0.02749   0.02110  -0.0451   0.0446   1.0000
  12.750   1.5199   0.02894   0.02262  -0.0438   0.0416   1.0000
  13.000   1.5219   0.03088   0.02459  -0.0424   0.0387   1.0000
  13.250   1.5248   0.03283   0.02663  -0.0412   0.0365   1.0000
  13.500   1.5306   0.03460   0.02849  -0.0403   0.0343   1.0000
  13.750   1.5318   0.03688   0.03081  -0.0395   0.0323   1.0000
  14.000   1.5252   0.04005   0.03405  -0.0387   0.0305   1.0000
  14.250   1.5299   0.04219   0.03631  -0.0382   0.0292   1.0000
  14.500   1.5322   0.04464   0.03887  -0.0380   0.0277   1.0000
  14.750   1.5309   0.04758   0.04189  -0.0379   0.0265   1.0000
  15.000   1.5254   0.05117   0.04555  -0.0381   0.0254   1.0000
  15.250   1.5135   0.05570   0.05018  -0.0386   0.0244   1.0000
  15.500   1.5149   0.05873   0.05334  -0.0391   0.0236   1.0000
  15.750   1.5135   0.06222   0.05695  -0.0398   0.0227   1.0000
  16.000   1.5105   0.06604   0.06087  -0.0407   0.0218   1.0000
  16.250   1.5050   0.07034   0.06526  -0.0419   0.0212   1.0000
  16.500   1.4964   0.07524   0.07025  -0.0435   0.0205   1.0000
  16.750   1.4839   0.08084   0.07594  -0.0454   0.0199   1.0000
  17.000   1.4725   0.08640   0.08162  -0.0474   0.0194   1.0000
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