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SD8000-089-88 (sd8000-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: SD8000-089-88 (sd8000-il)
Reynolds number: 500,000
Max Cl/Cd: 80.56 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd8000-il-500000.txt
Download as CSV file: xf-sd8000-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD8000-089-88                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.6598   0.07127   0.06900  -0.0304   1.0000   0.0127
 -10.500  -0.7192   0.04914   0.04655  -0.0502   1.0000   0.0120
 -10.250  -0.7456   0.04357   0.04084  -0.0540   1.0000   0.0118
 -10.000  -0.7624   0.03881   0.03577  -0.0547   1.0000   0.0119
  -9.750  -0.7696   0.03444   0.03102  -0.0544   1.0000   0.0119
  -9.500  -0.7677   0.03099   0.02720  -0.0534   1.0000   0.0119
  -9.250  -0.7595   0.02852   0.02439  -0.0520   1.0000   0.0120
  -9.000  -0.7491   0.02646   0.02204  -0.0504   1.0000   0.0121
  -8.750  -0.7451   0.02302   0.01820  -0.0481   1.0000   0.0124
  -8.500  -0.7329   0.02131   0.01634  -0.0462   1.0000   0.0129
  -8.250  -0.7166   0.02050   0.01546  -0.0446   1.0000   0.0134
  -8.000  -0.6998   0.01969   0.01455  -0.0429   1.0000   0.0140
  -7.750  -0.6830   0.01868   0.01339  -0.0413   1.0000   0.0146
  -7.500  -0.6656   0.01763   0.01217  -0.0396   1.0000   0.0152
  -7.250  -0.6471   0.01675   0.01114  -0.0381   1.0000   0.0157
  -7.000  -0.6295   0.01538   0.00960  -0.0366   1.0000   0.0167
  -6.750  -0.5999   0.01457   0.00875  -0.0374   0.9985   0.0181
  -6.500  -0.5658   0.01394   0.00803  -0.0390   0.9963   0.0199
  -6.250  -0.5318   0.01306   0.00707  -0.0406   0.9943   0.0228
  -6.000  -0.4984   0.01273   0.00672  -0.0419   0.9917   0.0262
  -5.750  -0.4652   0.01204   0.00599  -0.0432   0.9888   0.0305
  -5.500  -0.4297   0.01178   0.00568  -0.0449   0.9864   0.0348
  -5.250  -0.3940   0.01124   0.00516  -0.0467   0.9845   0.0418
  -5.000  -0.3595   0.01083   0.00475  -0.0482   0.9820   0.0493
  -4.750  -0.3265   0.01060   0.00448  -0.0493   0.9783   0.0564
  -4.500  -0.2909   0.01022   0.00412  -0.0510   0.9754   0.0672
  -4.250  -0.2536   0.00985   0.00379  -0.0531   0.9733   0.0794
  -4.000  -0.2154   0.00953   0.00350  -0.0553   0.9716   0.0938
  -3.750  -0.1830   0.00922   0.00325  -0.0562   0.9675   0.1110
  -3.500  -0.1508   0.00891   0.00303  -0.0572   0.9629   0.1348
  -3.250  -0.1171   0.00857   0.00282  -0.0584   0.9591   0.1683
  -3.000  -0.0873   0.00825   0.00264  -0.0587   0.9537   0.2104
  -2.750  -0.0596   0.00790   0.00249  -0.0587   0.9469   0.2609
  -2.500  -0.0318   0.00757   0.00235  -0.0585   0.9407   0.3181
  -2.250  -0.0066   0.00725   0.00222  -0.0579   0.9322   0.3821
  -2.000   0.0190   0.00695   0.00212  -0.0572   0.9246   0.4452
  -1.750   0.0440   0.00666   0.00203  -0.0564   0.9158   0.5122
  -1.500   0.0690   0.00641   0.00197  -0.0556   0.9066   0.5741
  -1.250   0.0944   0.00619   0.00189  -0.0547   0.8981   0.6310
  -1.000   0.1193   0.00599   0.00186  -0.0537   0.8869   0.6861
  -0.750   0.1442   0.00582   0.00182  -0.0527   0.8755   0.7361
  -0.500   0.1690   0.00567   0.00179  -0.0516   0.8635   0.7819
  -0.250   0.1936   0.00556   0.00176  -0.0504   0.8506   0.8245
   0.000   0.2176   0.00546   0.00173  -0.0491   0.8366   0.8651
   0.250   0.2413   0.00539   0.00171  -0.0476   0.8212   0.9047
   0.500   0.2682   0.00536   0.00168  -0.0468   0.8039   0.9420
   0.750   0.3042   0.00536   0.00162  -0.0482   0.7837   0.9705
   1.000   0.3456   0.00540   0.00156  -0.0508   0.7608   0.9896
   1.250   0.3813   0.00548   0.00152  -0.0524   0.7349   1.0000
   1.500   0.4049   0.00560   0.00152  -0.0514   0.7073   1.0000
   1.750   0.4290   0.00576   0.00154  -0.0505   0.6775   1.0000
   2.000   0.4535   0.00594   0.00158  -0.0498   0.6452   1.0000
   2.250   0.4782   0.00614   0.00163  -0.0490   0.6102   1.0000
   2.500   0.5030   0.00637   0.00170  -0.0483   0.5746   1.0000
   2.750   0.5281   0.00662   0.00181  -0.0477   0.5367   1.0000
   3.000   0.5531   0.00690   0.00192  -0.0472   0.4993   1.0000
   3.250   0.5783   0.00718   0.00205  -0.0466   0.4607   1.0000
   3.500   0.6034   0.00749   0.00220  -0.0461   0.4214   1.0000
   3.750   0.6287   0.00781   0.00237  -0.0457   0.3848   1.0000
   4.000   0.6538   0.00815   0.00255  -0.0452   0.3474   1.0000
   4.250   0.6790   0.00850   0.00275  -0.0448   0.3117   1.0000
   4.500   0.7042   0.00887   0.00298  -0.0444   0.2789   1.0000
   4.750   0.7295   0.00922   0.00321  -0.0440   0.2498   1.0000
   5.000   0.7548   0.00959   0.00345  -0.0436   0.2218   1.0000
   5.250   0.7802   0.00993   0.00372  -0.0432   0.1979   1.0000
   5.500   0.8054   0.01031   0.00401  -0.0428   0.1762   1.0000
   5.750   0.8307   0.01068   0.00430  -0.0424   0.1558   1.0000
   6.000   0.8555   0.01110   0.00462  -0.0420   0.1371   1.0000
   6.250   0.8805   0.01149   0.00496  -0.0415   0.1198   1.0000
   6.500   0.9055   0.01188   0.00530  -0.0411   0.1057   1.0000
   6.750   0.9302   0.01229   0.00567  -0.0407   0.0933   1.0000
   7.000   0.9546   0.01274   0.00607  -0.0402   0.0819   1.0000
   7.250   0.9794   0.01313   0.00647  -0.0397   0.0726   1.0000
   7.500   1.0039   0.01355   0.00689  -0.0392   0.0638   1.0000
   7.750   1.0277   0.01404   0.00737  -0.0386   0.0548   1.0000
   8.000   1.0509   0.01462   0.00791  -0.0380   0.0457   1.0000
   8.250   1.0729   0.01534   0.00859  -0.0372   0.0370   1.0000
   8.500   1.0960   0.01590   0.00919  -0.0365   0.0318   1.0000
   8.750   1.1164   0.01678   0.01012  -0.0354   0.0277   1.0000
   9.000   1.1386   0.01739   0.01079  -0.0346   0.0253   1.0000
   9.250   1.1578   0.01835   0.01177  -0.0334   0.0229   1.0000
   9.500   1.1765   0.01931   0.01284  -0.0321   0.0215   1.0000
   9.750   1.1965   0.02009   0.01372  -0.0311   0.0204   1.0000
  10.000   1.2155   0.02092   0.01465  -0.0299   0.0195   1.0000
  10.250   1.2336   0.02180   0.01559  -0.0287   0.0185   1.0000
  10.500   1.2484   0.02297   0.01682  -0.0271   0.0176   1.0000
  10.750   1.2565   0.02488   0.01887  -0.0247   0.0167   1.0000
  11.000   1.2730   0.02574   0.01985  -0.0233   0.0162   1.0000
  11.250   1.2864   0.02684   0.02108  -0.0216   0.0157   1.0000
  11.500   1.2957   0.02804   0.02242  -0.0193   0.0153   1.0000
  11.750   1.3033   0.02924   0.02374  -0.0168   0.0147   1.0000
  12.000   1.3090   0.03060   0.02521  -0.0144   0.0144   1.0000
  12.250   1.3148   0.03190   0.02661  -0.0123   0.0139   1.0000
  12.500   1.3178   0.03355   0.02836  -0.0102   0.0136   1.0000
  12.750   1.3191   0.03540   0.03029  -0.0084   0.0132   1.0000
  13.000   1.3111   0.03849   0.03355  -0.0065   0.0128   1.0000
  13.250   1.2979   0.04251   0.03779  -0.0050   0.0126   1.0000
  13.500   1.2954   0.04512   0.04058  -0.0044   0.0124   1.0000
  13.750   1.2964   0.04736   0.04299  -0.0045   0.0121   1.0000
  14.000   1.2894   0.05103   0.04683  -0.0050   0.0120   1.0000
  14.250   1.2804   0.05527   0.05126  -0.0061   0.0119   1.0000
  14.500   1.2685   0.06027   0.05644  -0.0081   0.0119   1.0000
  14.750   1.2569   0.06564   0.06199  -0.0108   0.0117   1.0000
  15.000   1.2438   0.07162   0.06814  -0.0141   0.0116   1.0000
  15.250   1.2252   0.07903   0.07574  -0.0185   0.0116   1.0000
  15.500   1.2066   0.08690   0.08378  -0.0233   0.0117   1.0000
  15.750   1.1867   0.09555   0.09260  -0.0288   0.0116   1.0000
  16.000   1.1619   0.10559   0.10281  -0.0351   0.0118   1.0000
  16.250   1.1353   0.11668   0.11407  -0.0421   0.0120   1.0000
  16.500   1.1056   0.12908   0.12662  -0.0499   0.0121   1.0000
  16.750   1.0684   0.14422   0.14191  -0.0592   0.0124   1.0000
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