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=1,000,000 Ncrit=5


Details Polar file
Airfoil: SD8000-089-88 (sd8000-il)
Reynolds number: 1,000,000
Max Cl/Cd: 87.59 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd8000-il-1000000-n5.txt
Download as CSV file: xf-sd8000-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.8567   0.08434   0.08219  -0.0240   1.0000   0.0039
 -13.750  -0.9560   0.06247   0.06019  -0.0378   1.0000   0.0038
 -13.500  -1.0408   0.03923   0.03654  -0.0576   1.0000   0.0036
 -13.250  -1.0672   0.03437   0.03149  -0.0597   1.0000   0.0036
 -13.000  -1.0740   0.03198   0.02894  -0.0582   1.0000   0.0036
 -12.750  -1.0710   0.02974   0.02653  -0.0575   1.0000   0.0036
 -12.500  -1.0628   0.02779   0.02441  -0.0567   1.0000   0.0037
 -12.250  -1.0503   0.02620   0.02266  -0.0561   1.0000   0.0037
 -12.000  -1.0358   0.02471   0.02102  -0.0554   1.0000   0.0038
 -11.750  -1.0191   0.02342   0.01959  -0.0547   1.0000   0.0039
 -11.500  -1.0014   0.02222   0.01825  -0.0541   1.0000   0.0039
 -11.250  -0.9821   0.02123   0.01713  -0.0534   1.0000   0.0040
 -11.000  -0.9628   0.02020   0.01597  -0.0527   1.0000   0.0040
 -10.750  -0.9425   0.01936   0.01503  -0.0520   1.0000   0.0041
 -10.500  -0.9224   0.01857   0.01414  -0.0511   1.0000   0.0041
 -10.250  -0.9052   0.01744   0.01287  -0.0499   1.0000   0.0043
 -10.000  -0.8826   0.01650   0.01181  -0.0495   0.9989   0.0044
  -9.750  -0.8538   0.01565   0.01085  -0.0504   0.9962   0.0047
  -9.500  -0.8241   0.01494   0.01005  -0.0513   0.9939   0.0048
  -9.250  -0.7952   0.01430   0.00933  -0.0519   0.9911   0.0050
  -9.000  -0.7656   0.01373   0.00868  -0.0527   0.9884   0.0053
  -8.750  -0.7352   0.01320   0.00808  -0.0535   0.9859   0.0055
  -8.500  -0.7043   0.01269   0.00750  -0.0544   0.9838   0.0058
  -8.250  -0.6760   0.01225   0.00700  -0.0547   0.9797   0.0061
  -8.000  -0.6472   0.01181   0.00649  -0.0551   0.9756   0.0065
  -7.750  -0.6181   0.01134   0.00598  -0.0556   0.9719   0.0072
  -7.500  -0.5908   0.01096   0.00557  -0.0556   0.9673   0.0080
  -7.250  -0.5638   0.01063   0.00520  -0.0554   0.9620   0.0087
  -7.000  -0.5368   0.01029   0.00482  -0.0553   0.9572   0.0100
  -6.750  -0.5107   0.00999   0.00449  -0.0549   0.9515   0.0117
  -6.500  -0.4844   0.00970   0.00419  -0.0546   0.9459   0.0136
  -6.250  -0.4580   0.00945   0.00391  -0.0542   0.9409   0.0156
  -6.000  -0.4314   0.00920   0.00364  -0.0540   0.9350   0.0177
  -5.750  -0.4050   0.00897   0.00339  -0.0536   0.9294   0.0204
  -5.500  -0.3782   0.00873   0.00315  -0.0533   0.9236   0.0236
  -5.250  -0.3515   0.00853   0.00293  -0.0530   0.9169   0.0267
  -5.000  -0.3246   0.00833   0.00272  -0.0527   0.9106   0.0307
  -4.750  -0.2975   0.00814   0.00252  -0.0525   0.9035   0.0353
  -4.500  -0.2706   0.00794   0.00234  -0.0523   0.8969   0.0431
  -4.250  -0.2432   0.00777   0.00217  -0.0521   0.8892   0.0490
  -4.000  -0.2159   0.00762   0.00200  -0.0518   0.8815   0.0548
  -3.750  -0.1885   0.00747   0.00185  -0.0517   0.8724   0.0616
  -3.500  -0.1610   0.00734   0.00171  -0.0515   0.8629   0.0693
  -3.250  -0.1337   0.00721   0.00158  -0.0512   0.8524   0.0793
  -3.000  -0.1063   0.00707   0.00145  -0.0511   0.8403   0.0919
  -2.750  -0.0788   0.00695   0.00133  -0.0509   0.8271   0.1068
  -2.500  -0.0514   0.00684   0.00123  -0.0507   0.8126   0.1213
  -2.250  -0.0240   0.00673   0.00112  -0.0505   0.7970   0.1413
  -2.000   0.0033   0.00663   0.00104  -0.0503   0.7802   0.1624
  -1.750   0.0307   0.00653   0.00096  -0.0501   0.7612   0.1897
  -1.500   0.0579   0.00646   0.00089  -0.0499   0.7387   0.2156
  -1.250   0.0850   0.00642   0.00084  -0.0497   0.7137   0.2436
  -1.000   0.1120   0.00635   0.00080  -0.0495   0.6889   0.2823
  -0.750   0.1391   0.00628   0.00077  -0.0494   0.6639   0.3245
  -0.500   0.1662   0.00622   0.00075  -0.0492   0.6378   0.3692
  -0.250   0.1932   0.00617   0.00075  -0.0491   0.6107   0.4155
   0.000   0.2201   0.00615   0.00076  -0.0489   0.5807   0.4627
   0.500   0.2738   0.00617   0.00082  -0.0485   0.5194   0.5539
   0.750   0.3006   0.00619   0.00087  -0.0483   0.4897   0.6011
   1.000   0.3273   0.00623   0.00093  -0.0481   0.4598   0.6448
   1.250   0.3539   0.00629   0.00100  -0.0478   0.4295   0.6871
   1.500   0.3802   0.00637   0.00108  -0.0475   0.3981   0.7291
   1.750   0.4063   0.00646   0.00118  -0.0471   0.3672   0.7703
   2.000   0.4323   0.00655   0.00128  -0.0467   0.3389   0.8076
   2.250   0.4579   0.00665   0.00138  -0.0461   0.3123   0.8422
   2.500   0.4829   0.00672   0.00148  -0.0454   0.2918   0.8796
   2.750   0.5065   0.00681   0.00160  -0.0443   0.2684   0.9213
   3.000   0.5352   0.00695   0.00170  -0.0443   0.2453   0.9634
   3.250   0.5719   0.00715   0.00181  -0.0463   0.2233   0.9971
   3.500   0.5990   0.00737   0.00194  -0.0462   0.2025   1.0000
   3.750   0.6255   0.00760   0.00208  -0.0460   0.1833   1.0000
   4.000   0.6520   0.00784   0.00223  -0.0457   0.1655   1.0000
   4.250   0.6785   0.00807   0.00240  -0.0455   0.1493   1.0000
   4.500   0.7050   0.00830   0.00256  -0.0452   0.1353   1.0000
   4.750   0.7316   0.00853   0.00274  -0.0450   0.1236   1.0000
   5.000   0.7582   0.00875   0.00292  -0.0448   0.1130   1.0000
   5.250   0.7844   0.00901   0.00313  -0.0445   0.1002   1.0000
   5.500   0.8104   0.00932   0.00335  -0.0442   0.0859   1.0000
   5.750   0.8364   0.00961   0.00358  -0.0439   0.0741   1.0000
   6.000   0.8625   0.00987   0.00382  -0.0437   0.0661   1.0000
   6.250   0.8884   0.01017   0.00408  -0.0434   0.0581   1.0000
   6.500   0.9144   0.01044   0.00433  -0.0431   0.0516   1.0000
   6.750   0.9402   0.01074   0.00461  -0.0427   0.0456   1.0000
   7.000   0.9655   0.01109   0.00492  -0.0424   0.0388   1.0000
   7.250   0.9910   0.01141   0.00523  -0.0420   0.0335   1.0000
   7.500   1.0161   0.01177   0.00557  -0.0416   0.0284   1.0000
   7.750   1.0409   0.01216   0.00594  -0.0412   0.0235   1.0000
   8.000   1.0657   0.01254   0.00631  -0.0408   0.0198   1.0000
   8.250   1.0901   0.01296   0.00674  -0.0403   0.0167   1.0000
   8.500   1.1146   0.01335   0.00714  -0.0398   0.0151   1.0000
   8.750   1.1386   0.01380   0.00761  -0.0392   0.0134   1.0000
   9.000   1.1626   0.01424   0.00807  -0.0387   0.0124   1.0000
   9.250   1.1866   0.01464   0.00852  -0.0382   0.0118   1.0000
   9.500   1.2101   0.01510   0.00902  -0.0376   0.0112   1.0000
   9.750   1.2331   0.01558   0.00954  -0.0369   0.0107   1.0000
  10.000   1.2556   0.01612   0.01012  -0.0362   0.0101   1.0000
  10.250   1.2771   0.01674   0.01080  -0.0354   0.0095   1.0000
  10.500   1.2990   0.01729   0.01140  -0.0346   0.0092   1.0000
  10.750   1.3210   0.01779   0.01196  -0.0339   0.0089   1.0000
  11.000   1.3423   0.01835   0.01259  -0.0330   0.0086   1.0000
  11.250   1.3630   0.01893   0.01323  -0.0321   0.0083   1.0000
  11.500   1.3832   0.01951   0.01387  -0.0312   0.0080   1.0000
  11.750   1.4025   0.02015   0.01457  -0.0302   0.0077   1.0000
  12.000   1.4208   0.02085   0.01532  -0.0290   0.0074   1.0000
  12.250   1.4374   0.02164   0.01618  -0.0276   0.0071   1.0000
  12.500   1.4512   0.02259   0.01724  -0.0259   0.0068   1.0000
  12.750   1.4646   0.02346   0.01819  -0.0242   0.0066   1.0000
  13.000   1.4772   0.02415   0.01895  -0.0221   0.0065   1.0000
  13.250   1.4874   0.02492   0.01981  -0.0199   0.0063   1.0000
  13.500   1.4954   0.02585   0.02083  -0.0175   0.0062   1.0000
  13.750   1.5037   0.02681   0.02187  -0.0154   0.0061   1.0000
  14.000   1.5116   0.02784   0.02299  -0.0134   0.0059   1.0000
  14.250   1.5186   0.02899   0.02422  -0.0116   0.0057   1.0000
  14.500   1.5249   0.03025   0.02556  -0.0099   0.0055   1.0000
  14.750   1.5277   0.03185   0.02727  -0.0082   0.0054   1.0000
  15.000   1.5312   0.03352   0.02903  -0.0069   0.0052   1.0000
  15.250   1.5322   0.03551   0.03112  -0.0058   0.0051   1.0000
  15.500   1.5314   0.03785   0.03355  -0.0050   0.0050   1.0000
  15.750   1.5293   0.04050   0.03630  -0.0047   0.0048   1.0000
  16.000   1.5231   0.04385   0.03978  -0.0049   0.0048   1.0000
  16.250   1.5145   0.04780   0.04387  -0.0058   0.0047   1.0000
  16.500   1.5013   0.05279   0.04901  -0.0076   0.0046   1.0000
  16.750   1.4844   0.05884   0.05521  -0.0104   0.0046   1.0000
  17.000   1.4724   0.06453   0.06105  -0.0134   0.0045   1.0000
  17.250   1.4464   0.07313   0.06982  -0.0183   0.0046   1.0000
  17.750   1.3821   0.09415   0.09121  -0.0306   0.0046   1.0000
  18.000   1.3476   0.10564   0.10287  -0.0373   0.0047   1.0000
  18.250   1.3119   0.11769   0.11509  -0.0443   0.0048   1.0000
<< Back to SD8000-089-88 (sd8000-il)

Polar data table (+)

Polar graphs


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