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SD8000-089-88 (sd8000-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: SD8000-089-88 (sd8000-il)
Reynolds number: 200,000
Max Cl/Cd: 57.87 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd8000-il-200000-n5.txt
Download as CSV file: xf-sd8000-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5481   0.09987   0.09615  -0.0153   1.0000   0.0140
 -10.500  -0.6987   0.05719   0.05346  -0.0418   1.0000   0.0122
 -10.250  -0.7218   0.04884   0.04495  -0.0506   1.0000   0.0121
 -10.000  -0.7403   0.04416   0.04004  -0.0524   1.0000   0.0120
  -9.750  -0.7521   0.03929   0.03475  -0.0531   1.0000   0.0121
  -9.500  -0.7537   0.03532   0.03034  -0.0527   1.0000   0.0122
  -9.250  -0.7477   0.03236   0.02708  -0.0519   1.0000   0.0125
  -9.000  -0.7360   0.03036   0.02489  -0.0509   1.0000   0.0128
  -8.750  -0.7229   0.02850   0.02281  -0.0498   1.0000   0.0132
  -8.500  -0.7085   0.02683   0.02091  -0.0485   1.0000   0.0137
  -8.250  -0.6934   0.02520   0.01901  -0.0471   1.0000   0.0144
  -8.000  -0.6775   0.02362   0.01717  -0.0457   1.0000   0.0151
  -7.750  -0.6601   0.02233   0.01560  -0.0443   1.0000   0.0163
  -7.500  -0.6425   0.02138   0.01461  -0.0430   1.0000   0.0175
  -7.250  -0.6238   0.02053   0.01364  -0.0417   1.0000   0.0189
  -7.000  -0.6052   0.01949   0.01241  -0.0403   1.0000   0.0203
  -6.750  -0.5864   0.01846   0.01127  -0.0390   1.0000   0.0220
  -6.500  -0.5664   0.01779   0.01052  -0.0379   1.0000   0.0241
  -6.250  -0.5456   0.01723   0.00982  -0.0367   1.0000   0.0271
  -6.000  -0.5143   0.01651   0.00907  -0.0379   0.9969   0.0311
  -5.750  -0.4812   0.01597   0.00841  -0.0393   0.9937   0.0359
  -5.500  -0.4493   0.01539   0.00780  -0.0404   0.9899   0.0414
  -5.250  -0.4162   0.01484   0.00718  -0.0417   0.9864   0.0474
  -5.000  -0.3816   0.01437   0.00666  -0.0433   0.9835   0.0541
  -4.750  -0.3507   0.01390   0.00619  -0.0442   0.9788   0.0619
  -4.500  -0.3173   0.01351   0.00573  -0.0454   0.9749   0.0707
  -4.250  -0.2821   0.01316   0.00536  -0.0471   0.9718   0.0823
  -4.000  -0.2499   0.01281   0.00503  -0.0481   0.9672   0.0957
  -3.750  -0.2170   0.01245   0.00470  -0.0493   0.9625   0.1116
  -3.500  -0.1821   0.01210   0.00442  -0.0509   0.9587   0.1333
  -3.250  -0.1502   0.01177   0.00418  -0.0518   0.9534   0.1592
  -3.000  -0.1189   0.01144   0.00395  -0.0526   0.9473   0.1934
  -2.750  -0.0849   0.01109   0.00374  -0.0539   0.9429   0.2364
  -2.500  -0.0572   0.01077   0.00359  -0.0539   0.9349   0.2851
  -2.250  -0.0257   0.01039   0.00342  -0.0547   0.9289   0.3468
  -2.000   0.0013   0.01006   0.00332  -0.0545   0.9201   0.4108
  -1.750   0.0310   0.00972   0.00321  -0.0547   0.9132   0.4827
  -1.500   0.0565   0.00944   0.00316  -0.0540   0.9026   0.5478
  -1.250   0.0830   0.00919   0.00310  -0.0533   0.8928   0.6094
  -1.000   0.1096   0.00895   0.00304  -0.0526   0.8831   0.6675
  -0.750   0.1342   0.00876   0.00301  -0.0513   0.8708   0.7221
  -0.500   0.1586   0.00859   0.00298  -0.0500   0.8583   0.7735
  -0.250   0.1830   0.00846   0.00294  -0.0486   0.8451   0.8208
   0.000   0.2086   0.00835   0.00289  -0.0473   0.8307   0.8656
   0.250   0.2385   0.00826   0.00281  -0.0470   0.8145   0.9085
   0.500   0.2746   0.00820   0.00270  -0.0482   0.7961   0.9456
   0.750   0.3136   0.00816   0.00260  -0.0502   0.7745   0.9767
   1.000   0.3503   0.00817   0.00249  -0.0518   0.7503   1.0000
   1.250   0.3745   0.00826   0.00245  -0.0508   0.7242   1.0000
   1.500   0.3989   0.00838   0.00243  -0.0499   0.6956   1.0000
   1.750   0.4233   0.00853   0.00244  -0.0490   0.6648   1.0000
   2.000   0.4478   0.00872   0.00247  -0.0482   0.6323   1.0000
   2.250   0.4723   0.00894   0.00253  -0.0473   0.5979   1.0000
   2.500   0.4967   0.00919   0.00262  -0.0465   0.5619   1.0000
   2.750   0.5211   0.00947   0.00273  -0.0458   0.5248   1.0000
   3.000   0.5453   0.00978   0.00286  -0.0450   0.4864   1.0000
   3.250   0.5696   0.01011   0.00303  -0.0443   0.4480   1.0000
   3.500   0.5938   0.01047   0.00323  -0.0437   0.4106   1.0000
   3.750   0.6183   0.01082   0.00344  -0.0431   0.3752   1.0000
   4.000   0.6427   0.01120   0.00367  -0.0425   0.3417   1.0000
   4.250   0.6672   0.01159   0.00394  -0.0419   0.3104   1.0000
   4.500   0.6916   0.01199   0.00423  -0.0414   0.2805   1.0000
   4.750   0.7162   0.01239   0.00453  -0.0409   0.2530   1.0000
   5.000   0.7407   0.01280   0.00485  -0.0404   0.2270   1.0000
   5.250   0.7651   0.01323   0.00521  -0.0399   0.2041   1.0000
   5.500   0.7895   0.01367   0.00558  -0.0394   0.1826   1.0000
   5.750   0.8137   0.01413   0.00598  -0.0389   0.1642   1.0000
   6.000   0.8380   0.01458   0.00640  -0.0384   0.1474   1.0000
   6.250   0.8622   0.01505   0.00686  -0.0378   0.1326   1.0000
   6.500   0.8861   0.01554   0.00734  -0.0373   0.1195   1.0000
   6.750   0.9098   0.01605   0.00784  -0.0367   0.1068   1.0000
   7.000   0.9332   0.01660   0.00837  -0.0361   0.0949   1.0000
   7.500   0.9795   0.01772   0.00950  -0.0349   0.0722   1.0000
   7.750   1.0024   0.01829   0.01011  -0.0343   0.0633   1.0000
   8.000   1.0247   0.01894   0.01078  -0.0335   0.0554   1.0000
   8.500   1.0680   0.02035   0.01229  -0.0320   0.0416   1.0000
   8.750   1.0879   0.02123   0.01319  -0.0310   0.0368   1.0000
   9.000   1.1081   0.02206   0.01414  -0.0300   0.0328   1.0000
   9.250   1.1257   0.02314   0.01524  -0.0288   0.0296   1.0000
   9.500   1.1444   0.02406   0.01630  -0.0276   0.0270   1.0000
   9.750   1.1623   0.02501   0.01736  -0.0264   0.0249   1.0000
  10.000   1.1779   0.02613   0.01858  -0.0251   0.0233   1.0000
  10.250   1.1906   0.02751   0.02005  -0.0233   0.0222   1.0000
  10.500   1.2044   0.02875   0.02146  -0.0217   0.0214   1.0000
  10.750   1.2165   0.03007   0.02294  -0.0200   0.0206   1.0000
  11.000   1.2261   0.03141   0.02443  -0.0179   0.0197   1.0000
  11.250   1.2340   0.03273   0.02588  -0.0158   0.0189   1.0000
  11.500   1.2402   0.03413   0.02739  -0.0137   0.0183   1.0000
  11.750   1.2442   0.03574   0.02913  -0.0117   0.0177   1.0000
  12.000   1.2435   0.03793   0.03141  -0.0097   0.0171   1.0000
  12.250   1.2458   0.03998   0.03365  -0.0081   0.0167   1.0000
  12.500   1.2460   0.04231   0.03620  -0.0068   0.0164   1.0000
  12.750   1.2442   0.04496   0.03907  -0.0059   0.0161   1.0000
  13.000   1.2405   0.04796   0.04229  -0.0054   0.0158   1.0000
  13.250   1.2350   0.05135   0.04588  -0.0054   0.0155   1.0000
  13.500   1.2275   0.05523   0.04997  -0.0061   0.0153   1.0000
  13.750   1.2183   0.05962   0.05457  -0.0075   0.0151   1.0000
  14.000   1.2071   0.06467   0.05982  -0.0097   0.0149   1.0000
  14.250   1.1945   0.07034   0.06569  -0.0127   0.0148   1.0000
  14.500   1.1794   0.07687   0.07242  -0.0165   0.0147   1.0000
  14.750   1.1606   0.08456   0.08032  -0.0212   0.0147   1.0000
  15.000   1.1393   0.09330   0.08927  -0.0267   0.0148   1.0000
  15.250   1.1140   0.10350   0.09967  -0.0332   0.0149   1.0000
  15.500   1.0828   0.11578   0.11214  -0.0410   0.0152   1.0000
  15.750   1.0417   0.13157   0.12811  -0.0507   0.0157   1.0000
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