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

SD8000-089-88 (sd8000-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: SD8000-089-88 (sd8000-il)
Reynolds number: 100,000
Max Cl/Cd: 46.65 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd8000-il-100000-n5.txt
Download as CSV file: xf-sd8000-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5368   0.09226   0.08711  -0.0217   1.0000   0.0265
  -9.750  -0.5434   0.08637   0.08128  -0.0247   1.0000   0.0265
  -9.500  -0.5516   0.08026   0.07525  -0.0282   1.0000   0.0264
  -9.250  -0.5642   0.07304   0.06813  -0.0327   1.0000   0.0261
  -9.000  -0.5857   0.06307   0.05820  -0.0411   1.0000   0.0256
  -8.750  -0.6078   0.05598   0.05099  -0.0461   1.0000   0.0251
  -8.500  -0.6249   0.04936   0.04405  -0.0486   1.0000   0.0251
  -8.250  -0.6333   0.04365   0.03789  -0.0492   1.0000   0.0253
  -8.000  -0.6339   0.03878   0.03248  -0.0486   1.0000   0.0258
  -7.750  -0.6284   0.03463   0.02772  -0.0475   1.0000   0.0266
  -7.500  -0.6172   0.03162   0.02427  -0.0462   1.0000   0.0278
  -7.250  -0.6005   0.03055   0.02317  -0.0452   1.0000   0.0298
  -7.000  -0.5840   0.02887   0.02117  -0.0439   1.0000   0.0325
  -6.750  -0.5667   0.02670   0.01849  -0.0425   1.0000   0.0351
  -6.500  -0.5489   0.02533   0.01709  -0.0414   1.0000   0.0379
  -6.250  -0.5294   0.02432   0.01589  -0.0402   1.0000   0.0422
  -6.000  -0.5096   0.02287   0.01416  -0.0389   1.0000   0.0461
  -5.750  -0.4899   0.02206   0.01335  -0.0379   1.0000   0.0509
  -5.500  -0.4689   0.02103   0.01205  -0.0366   1.0000   0.0559
  -5.250  -0.4487   0.02016   0.01120  -0.0356   1.0000   0.0616
  -5.000  -0.4273   0.01944   0.01029  -0.0345   1.0000   0.0686
  -4.750  -0.4065   0.01868   0.00959  -0.0335   1.0000   0.0757
  -4.500  -0.3850   0.01805   0.00887  -0.0325   1.0000   0.0846
  -4.250  -0.3633   0.01754   0.00829  -0.0316   1.0000   0.0952
  -4.000  -0.3416   0.01701   0.00778  -0.0307   1.0000   0.1070
  -3.750  -0.3196   0.01654   0.00733  -0.0299   1.0000   0.1210
  -3.500  -0.2916   0.01609   0.00692  -0.0304   0.9976   0.1400
  -3.250  -0.2566   0.01565   0.00655  -0.0322   0.9922   0.1685
  -3.000  -0.2217   0.01521   0.00626  -0.0340   0.9865   0.2067
  -2.750  -0.1867   0.01478   0.00605  -0.0358   0.9808   0.2624
  -2.500  -0.1525   0.01435   0.00588  -0.0375   0.9744   0.3355
  -2.250  -0.1178   0.01393   0.00580  -0.0391   0.9684   0.4252
  -2.000  -0.0853   0.01356   0.00578  -0.0400   0.9612   0.5200
  -1.750  -0.0510   0.01328   0.00579  -0.0410   0.9550   0.6130
  -1.500  -0.0202   0.01306   0.00581  -0.0411   0.9469   0.6942
  -1.250   0.0133   0.01290   0.00584  -0.0414   0.9404   0.7710
  -1.000   0.0449   0.01276   0.00581  -0.0413   0.9319   0.8410
  -0.750   0.0889   0.01264   0.00574  -0.0437   0.9261   0.9085
  -0.500   0.1419   0.01250   0.00556  -0.0484   0.9189   0.9672
  -0.250   0.1930   0.01237   0.00534  -0.0529   0.9117   1.0000
   0.000   0.2244   0.01231   0.00520  -0.0535   0.8992   1.0000
   0.250   0.2535   0.01226   0.00508  -0.0536   0.8852   1.0000
   0.500   0.2821   0.01221   0.00496  -0.0534   0.8706   1.0000
   0.750   0.3103   0.01215   0.00486  -0.0531   0.8551   1.0000
   1.000   0.3375   0.01211   0.00477  -0.0526   0.8379   1.0000
   1.250   0.3634   0.01209   0.00470  -0.0518   0.8181   1.0000
   1.500   0.3904   0.01205   0.00462  -0.0511   0.7979   1.0000
   1.750   0.4167   0.01205   0.00458  -0.0503   0.7756   1.0000
   2.000   0.4434   0.01206   0.00452  -0.0495   0.7517   1.0000
   2.250   0.4692   0.01211   0.00450  -0.0486   0.7242   1.0000
   2.500   0.4950   0.01220   0.00449  -0.0477   0.6941   1.0000
   2.750   0.5203   0.01234   0.00454  -0.0467   0.6613   1.0000
   3.000   0.5452   0.01253   0.00461  -0.0458   0.6255   1.0000
   3.250   0.5698   0.01277   0.00471  -0.0448   0.5881   1.0000
   3.500   0.5939   0.01307   0.00487  -0.0438   0.5481   1.0000
   3.750   0.6177   0.01342   0.00506  -0.0428   0.5071   1.0000
   4.000   0.6412   0.01382   0.00529  -0.0418   0.4658   1.0000
   4.250   0.6644   0.01426   0.00557  -0.0409   0.4253   1.0000
   4.500   0.6876   0.01474   0.00591  -0.0400   0.3858   1.0000
   4.750   0.7108   0.01524   0.00628  -0.0392   0.3493   1.0000
   5.000   0.7338   0.01577   0.00669  -0.0384   0.3147   1.0000
   5.250   0.7569   0.01633   0.00715  -0.0376   0.2833   1.0000
   5.500   0.7798   0.01691   0.00764  -0.0369   0.2540   1.0000
   5.750   0.8027   0.01751   0.00817  -0.0362   0.2281   1.0000
   6.000   0.8253   0.01815   0.00874  -0.0354   0.2046   1.0000
   6.250   0.8480   0.01879   0.00935  -0.0347   0.1835   1.0000
   6.500   0.8701   0.01949   0.01003  -0.0339   0.1653   1.0000
   6.750   0.8923   0.02020   0.01073  -0.0331   0.1491   1.0000
   7.000   0.9143   0.02094   0.01148  -0.0324   0.1342   1.0000
   7.250   0.9358   0.02174   0.01229  -0.0315   0.1211   1.0000
   7.500   0.9567   0.02257   0.01316  -0.0307   0.1086   1.0000
   7.750   0.9776   0.02342   0.01407  -0.0298   0.0969   1.0000
   8.000   0.9983   0.02429   0.01502  -0.0289   0.0856   1.0000
   8.250   1.0182   0.02525   0.01606  -0.0279   0.0757   1.0000
   8.500   1.0369   0.02630   0.01717  -0.0269   0.0671   1.0000
   8.750   1.0549   0.02739   0.01832  -0.0258   0.0595   1.0000
   9.000   1.0727   0.02864   0.01974  -0.0246   0.0532   1.0000
   9.250   1.0885   0.02994   0.02108  -0.0233   0.0485   1.0000
   9.500   1.1045   0.03139   0.02272  -0.0220   0.0439   1.0000
   9.750   1.1194   0.03278   0.02423  -0.0206   0.0404   1.0000
  10.000   1.1313   0.03449   0.02599  -0.0191   0.0381   1.0000
  10.250   1.1444   0.03645   0.02822  -0.0176   0.0363   1.0000
  10.500   1.1560   0.03846   0.03051  -0.0160   0.0344   1.0000
  10.750   1.1652   0.04036   0.03262  -0.0144   0.0327   1.0000
  11.000   1.1708   0.04208   0.03447  -0.0124   0.0312   1.0000
  11.250   1.1743   0.04396   0.03643  -0.0105   0.0300   1.0000
  11.500   1.1748   0.04651   0.03914  -0.0087   0.0291   1.0000
  11.750   1.1724   0.04934   0.04229  -0.0070   0.0286   1.0000
  12.000   1.1660   0.05257   0.04585  -0.0056   0.0280   1.0000
  12.250   1.1563   0.05624   0.04981  -0.0049   0.0277   1.0000
  12.500   1.1435   0.06042   0.05427  -0.0050   0.0274   1.0000
  12.750   1.1276   0.06533   0.05945  -0.0062   0.0272   1.0000
  13.000   1.1086   0.07117   0.06554  -0.0087   0.0272   1.0000
  13.250   1.0866   0.07818   0.07279  -0.0128   0.0272   1.0000
  13.500   1.0611   0.08674   0.08157  -0.0185   0.0274   1.0000
  13.750   1.0312   0.09734   0.09236  -0.0259   0.0278   1.0000
  14.000   0.9965   0.11037   0.10552  -0.0348   0.0284   1.0000
  14.250   0.9576   0.12586   0.12106  -0.0444   0.0289   1.0000
<< Back to SD8000-089-88 (sd8000-il)

Polar data table (+)

Polar graphs


<< Back to SD8000-089-88 (sd8000-il)