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GIII BL0 AIRFOIL (giiia-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GIII BL0 AIRFOIL (giiia-il)
Reynolds number: 200,000
Max Cl/Cd: 49.74 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-giiia-il-200000.txt
Download as CSV file: xf-giiia-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GIII BL0 AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.4840   0.09949   0.09618  -0.0153   1.0000   0.0652
 -10.500  -0.4952   0.09379   0.09052  -0.0180   1.0000   0.0673
  -8.750  -0.7787   0.04810   0.04325  -0.0188   1.0000   0.0346
  -8.500  -0.7814   0.04391   0.03875  -0.0156   1.0000   0.0340
  -8.250  -0.7806   0.04048   0.03495  -0.0121   1.0000   0.0342
  -8.000  -0.7774   0.03734   0.03143  -0.0085   1.0000   0.0343
  -7.750  -0.7724   0.03411   0.02782  -0.0050   1.0000   0.0341
  -7.500  -0.7643   0.03127   0.02460  -0.0016   1.0000   0.0341
  -7.250  -0.7529   0.02898   0.02194   0.0015   1.0000   0.0345
  -7.000  -0.7392   0.02727   0.01990   0.0043   1.0000   0.0351
  -6.750  -0.7241   0.02458   0.01694   0.0064   1.0000   0.0369
  -6.500  -0.7073   0.02331   0.01565   0.0082   1.0000   0.0393
  -6.250  -0.6890   0.02212   0.01430   0.0101   1.0000   0.0413
  -6.000  -0.6700   0.02097   0.01302   0.0120   1.0000   0.0435
  -5.750  -0.6516   0.02032   0.01220   0.0139   1.0000   0.0459
  -5.500  -0.6340   0.01872   0.01066   0.0156   1.0000   0.0504
  -5.250  -0.6165   0.01797   0.00987   0.0176   1.0000   0.0547
  -5.000  -0.6000   0.01705   0.00892   0.0197   1.0000   0.0598
  -4.750  -0.5832   0.01642   0.00830   0.0217   1.0000   0.0680
  -4.500  -0.5668   0.01565   0.00757   0.0237   1.0000   0.0782
  -4.250  -0.5492   0.01502   0.00699   0.0255   1.0000   0.0967
  -4.000  -0.5326   0.01422   0.00647   0.0273   1.0000   0.1358
  -3.750  -0.5150   0.01355   0.00612   0.0289   1.0000   0.1980
  -3.500  -0.4973   0.01291   0.00578   0.0303   1.0000   0.2621
  -3.250  -0.4835   0.01178   0.00538   0.0322   1.0000   0.4026
  -3.000  -0.4660   0.01065   0.00541   0.0342   0.9978   0.6605
  -2.750  -0.4304   0.01048   0.00564   0.0332   0.9935   0.7641
  -2.500  -0.3937   0.01067   0.00597   0.0323   0.9879   0.8299
  -2.250  -0.3524   0.01105   0.00634   0.0304   0.9834   0.8706
  -2.000  -0.3133   0.01144   0.00667   0.0288   0.9773   0.8964
  -1.750  -0.2679   0.01184   0.00698   0.0259   0.9724   0.9137
  -1.500  -0.2110   0.01226   0.00730   0.0205   0.9695   0.9230
  -1.250  -0.1562   0.01248   0.00742   0.0156   0.9618   0.9305
  -1.000  -0.0836   0.01261   0.00746   0.0070   0.9573   0.9332
  -0.750  -0.0262   0.01263   0.00742   0.0015   0.9490   0.9397
  -0.500   0.0337   0.01257   0.00730  -0.0044   0.9407   0.9445
  -0.250   0.0807   0.01244   0.00714  -0.0078   0.9273   0.9498
   0.000   0.1140   0.01227   0.00693  -0.0086   0.9113   0.9571
   0.250   0.1527   0.01206   0.00668  -0.0105   0.8923   0.9614
   0.500   0.1815   0.01192   0.00650  -0.0103   0.8700   0.9696
   0.750   0.2193   0.01169   0.00621  -0.0121   0.8447   0.9739
   1.000   0.2537   0.01153   0.00599  -0.0133   0.8178   0.9804
   1.250   0.2900   0.01135   0.00574  -0.0150   0.7863   0.9858
   1.500   0.3268   0.01119   0.00547  -0.0168   0.7470   0.9911
   1.750   0.3633   0.01109   0.00519  -0.0186   0.7040   0.9959
   2.000   0.4004   0.01108   0.00497  -0.0206   0.6612   1.0000
   2.250   0.4231   0.01117   0.00488  -0.0198   0.6233   1.0000
   2.500   0.4459   0.01129   0.00484  -0.0191   0.5845   1.0000
   2.750   0.4685   0.01146   0.00484  -0.0183   0.5406   1.0000
   3.000   0.4906   0.01170   0.00485  -0.0175   0.4844   1.0000
   3.250   0.5118   0.01213   0.00489  -0.0166   0.3927   1.0000
   3.500   0.5328   0.01274   0.00509  -0.0158   0.3198   1.0000
   3.750   0.5548   0.01317   0.00531  -0.0151   0.2899   1.0000
   4.000   0.5772   0.01353   0.00557  -0.0144   0.2745   1.0000
   4.250   0.5994   0.01392   0.00586  -0.0136   0.2644   1.0000
   4.500   0.6221   0.01423   0.00617  -0.0129   0.2559   1.0000
   4.750   0.6447   0.01463   0.00653  -0.0121   0.2496   1.0000
   5.000   0.6676   0.01494   0.00688  -0.0114   0.2442   1.0000
   5.250   0.6905   0.01534   0.00727  -0.0106   0.2397   1.0000
   5.500   0.7136   0.01582   0.00776  -0.0099   0.2359   1.0000
   5.750   0.7360   0.01611   0.00817  -0.0090   0.2304   1.0000
   6.000   0.7572   0.01651   0.00853  -0.0081   0.2211   1.0000
   6.250   0.7772   0.01669   0.00875  -0.0069   0.2095   1.0000
   6.500   0.7973   0.01685   0.00902  -0.0057   0.1990   1.0000
   6.750   0.8171   0.01706   0.00931  -0.0045   0.1886   1.0000
   7.000   0.8363   0.01722   0.00953  -0.0031   0.1770   1.0000
   7.250   0.8557   0.01721   0.00966  -0.0017   0.1620   1.0000
   7.500   0.8724   0.01754   0.00958   0.0000   0.0673   1.0000
   7.750   0.8825   0.01908   0.01099   0.0029   0.0456   1.0000
   8.000   0.8926   0.02035   0.01235   0.0058   0.0396   1.0000
   8.250   0.9055   0.02125   0.01338   0.0084   0.0362   1.0000
   8.500   0.9154   0.02231   0.01449   0.0112   0.0330   1.0000
   8.750   0.9186   0.02405   0.01622   0.0149   0.0308   1.0000
   9.000   0.9306   0.02507   0.01736   0.0175   0.0297   1.0000
   9.250   0.9420   0.02629   0.01868   0.0202   0.0286   1.0000
   9.500   0.9538   0.02766   0.02014   0.0226   0.0276   1.0000
   9.750   0.9664   0.02917   0.02174   0.0249   0.0268   1.0000
  10.000   0.9783   0.03067   0.02335   0.0271   0.0258   1.0000
  10.250   0.9890   0.03226   0.02501   0.0293   0.0247   1.0000
  10.500   1.0005   0.03509   0.02791   0.0309   0.0235   1.0000
  11.000   1.0121   0.04083   0.03416   0.0356   0.0230   1.0000
  11.250   1.0132   0.04318   0.03677   0.0384   0.0229   1.0000
  11.500   1.0101   0.04583   0.03966   0.0414   0.0229   1.0000
  11.750   1.0032   0.04892   0.04297   0.0444   0.0230   1.0000
  12.000   0.9964   0.05196   0.04624   0.0469   0.0231   1.0000
  12.250   0.9880   0.05433   0.04881   0.0489   0.0232   1.0000
  12.500   0.9783   0.05690   0.05157   0.0502   0.0234   1.0000
  12.750   0.9668   0.05980   0.05468   0.0507   0.0235   1.0000
  13.000   0.9526   0.06331   0.05840   0.0502   0.0237   1.0000
  13.250   0.9347   0.06781   0.06315   0.0481   0.0241   1.0000
  13.500   0.9105   0.07410   0.06971   0.0442   0.0245   1.0000
  13.750   0.8767   0.08308   0.07897   0.0373   0.0250   1.0000
  14.000   0.8353   0.09537   0.09152   0.0278   0.0256   1.0000
  14.250   0.7058   0.09185   0.08812   0.0371   0.0256   1.0000
  14.500   0.6402   0.10809   0.10455   0.0275   0.0271   1.0000
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