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DEFIANT CANARD BL110 AIRFOIL (defcnd2-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: DEFIANT CANARD BL110 AIRFOIL (defcnd2-il)
Reynolds number: 200,000
Max Cl/Cd: 64.5 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-defcnd2-il-200000.txt
Download as CSV file: xf-defcnd2-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DEFIANT CANARD BL110 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.2882   0.10347   0.10028  -0.0478   1.0000   0.0522
 -10.000  -0.2953   0.10218   0.09908  -0.0454   1.0000   0.0534
  -9.750  -0.3030   0.10049   0.09746  -0.0443   0.9982   0.0550
  -9.500  -0.2913   0.09501   0.09198  -0.0512   0.9918   0.0579
  -9.250  -0.3041   0.08422   0.08120  -0.0726   0.9803   0.0603
  -9.000  -0.3157   0.07735   0.07413  -0.0842   0.9691   0.0606
  -8.750  -0.2779   0.07362   0.07061  -0.0795   0.9700   0.0627
  -8.500  -0.2597   0.07046   0.06745  -0.0819   0.9636   0.0643
  -8.250  -0.2496   0.06495   0.06185  -0.0895   0.9561   0.0665
  -8.000  -0.2486   0.06006   0.05682  -0.0943   0.9446   0.0686
  -7.750  -0.2245   0.04054   0.03710  -0.0976   0.9154   0.0753
  -7.500  -0.2086   0.03767   0.03422  -0.0974   0.9088   0.0769
  -7.250  -0.2058   0.03518   0.03166  -0.0958   0.8981   0.0790
  -7.000  -0.2051   0.03243   0.02872  -0.0940   0.8887   0.0822
  -6.750  -0.2371   0.04317   0.03854  -0.0944   0.8951   0.0883
  -6.500  -0.2382   0.03247   0.02687  -0.0892   0.8858   0.0467
  -6.250  -0.2263   0.02820   0.02197  -0.0865   0.8789   0.0424
  -6.000  -0.2099   0.02654   0.02004  -0.0845   0.8698   0.0428
  -5.750  -0.1874   0.02453   0.01763  -0.0832   0.8634   0.0428
  -5.500  -0.1673   0.02274   0.01550  -0.0814   0.8547   0.0422
  -5.250  -0.1407   0.02127   0.01380  -0.0807   0.8483   0.0423
  -5.000  -0.1177   0.02020   0.01260  -0.0795   0.8394   0.0433
  -4.750  -0.0905   0.01916   0.01141  -0.0790   0.8326   0.0446
  -4.500  -0.0677   0.01849   0.01066  -0.0777   0.8229   0.0471
  -4.250  -0.0414   0.01792   0.00995  -0.0770   0.8152   0.0492
  -4.000  -0.0208   0.01672   0.00878  -0.0755   0.8055   0.0521
  -3.750   0.0014   0.01611   0.00815  -0.0742   0.7964   0.0559
  -3.500   0.0243   0.01553   0.00749  -0.0729   0.7878   0.0616
  -3.250   0.0441   0.01494   0.00693  -0.0712   0.7777   0.0742
  -3.000   0.0605   0.01379   0.00620  -0.0690   0.7691   0.1554
  -2.750   0.0742   0.01279   0.00584  -0.0666   0.7586   0.3116
  -2.500   0.0815   0.01171   0.00569  -0.0627   0.7479   0.5336
  -2.250   0.0967   0.01129   0.00576  -0.0593   0.7382   0.7038
  -2.000   0.1181   0.01116   0.00576  -0.0570   0.7269   0.7720
  -1.750   0.1413   0.01115   0.00579  -0.0550   0.7148   0.8211
  -1.500   0.1672   0.01120   0.00580  -0.0536   0.7028   0.8566
  -1.250   0.1977   0.01129   0.00579  -0.0533   0.6908   0.8804
  -1.000   0.2321   0.01146   0.00581  -0.0537   0.6786   0.9019
  -0.750   0.2719   0.01166   0.00584  -0.0554   0.6657   0.9172
  -0.500   0.3188   0.01191   0.00590  -0.0586   0.6513   0.9293
  -0.250   0.3736   0.01222   0.00601  -0.0634   0.6354   0.9413
   0.000   0.4194   0.01242   0.00602  -0.0668   0.6188   0.9518
   0.250   0.4639   0.01253   0.00595  -0.0703   0.6030   0.9580
   0.500   0.5010   0.01264   0.00588  -0.0724   0.5885   0.9653
   0.750   0.5388   0.01273   0.00581  -0.0747   0.5744   0.9714
   1.000   0.5771   0.01283   0.00574  -0.0772   0.5607   0.9774
   1.250   0.6133   0.01294   0.00571  -0.0793   0.5476   0.9837
   1.500   0.6524   0.01301   0.00567  -0.0821   0.5346   0.9892
   1.750   0.6900   0.01311   0.00566  -0.0847   0.5226   0.9949
   2.000   0.7295   0.01320   0.00561  -0.0877   0.5124   1.0000
   2.250   0.7460   0.01329   0.00566  -0.0860   0.5039   1.0000
   2.500   0.7628   0.01341   0.00572  -0.0844   0.4967   1.0000
   2.750   0.7792   0.01351   0.00578  -0.0827   0.4896   1.0000
   3.000   0.7973   0.01367   0.00584  -0.0812   0.4842   1.0000
   3.250   0.8137   0.01378   0.00598  -0.0795   0.4781   1.0000
   3.500   0.8315   0.01393   0.00610  -0.0779   0.4728   1.0000
   3.750   0.8506   0.01414   0.00623  -0.0765   0.4684   1.0000
   4.000   0.8684   0.01431   0.00643  -0.0748   0.4632   1.0000
   4.250   0.8877   0.01449   0.00660  -0.0734   0.4585   1.0000
   4.500   0.9088   0.01473   0.00677  -0.0724   0.4547   1.0000
   4.750   0.9276   0.01494   0.00704  -0.0709   0.4500   1.0000
   5.000   0.9475   0.01516   0.00726  -0.0696   0.4455   1.0000
   5.250   0.9689   0.01539   0.00747  -0.0685   0.4416   1.0000
   5.500   0.9903   0.01567   0.00774  -0.0675   0.4376   1.0000
   5.750   1.0100   0.01592   0.00805  -0.0662   0.4331   1.0000
   6.000   1.0313   0.01616   0.00830  -0.0652   0.4288   1.0000
   6.250   1.0550   0.01647   0.00856  -0.0646   0.4250   1.0000
   6.500   1.0738   0.01675   0.00894  -0.0631   0.4203   1.0000
   6.750   1.0945   0.01703   0.00925  -0.0620   0.4156   1.0000
   7.000   1.1178   0.01733   0.00952  -0.0614   0.4114   1.0000
   7.250   1.1383   0.01769   0.00996  -0.0602   0.4069   1.0000
   7.500   1.1582   0.01802   0.01037  -0.0590   0.4022   1.0000
   7.750   1.1816   0.01837   0.01071  -0.0584   0.3980   1.0000
   8.000   1.2049   0.01882   0.01119  -0.0579   0.3939   1.0000
   8.250   1.2231   0.01923   0.01173  -0.0565   0.3892   1.0000
   8.500   1.2457   0.01965   0.01219  -0.0558   0.3851   1.0000
   8.750   1.2733   0.02016   0.01266  -0.0561   0.3814   1.0000
   9.000   1.2888   0.02063   0.01330  -0.0542   0.3764   1.0000
   9.250   1.3076   0.02093   0.01365  -0.0529   0.3703   1.0000
   9.500   1.3294   0.02133   0.01403  -0.0521   0.3640   1.0000
   9.750   1.3428   0.02169   0.01455  -0.0499   0.3583   1.0000
  10.000   1.3658   0.02207   0.01493  -0.0493   0.3534   1.0000
  10.250   1.3830   0.02253   0.01549  -0.0478   0.3479   1.0000
  10.500   1.3950   0.02287   0.01597  -0.0454   0.3421   1.0000
  10.750   1.4167   0.02311   0.01613  -0.0446   0.3350   1.0000
  11.000   1.4190   0.02343   0.01669  -0.0406   0.3293   1.0000
  11.250   1.4290   0.02356   0.01683  -0.0377   0.3223   1.0000
  11.500   1.4267   0.02385   0.01728  -0.0329   0.3160   1.0000
  11.750   1.4248   0.02408   0.01760  -0.0284   0.3085   1.0000
  12.000   1.4258   0.02453   0.01821  -0.0248   0.3018   1.0000
  12.250   1.4229   0.02499   0.01874  -0.0209   0.2924   1.0000
  12.500   1.4264   0.02575   0.01970  -0.0184   0.2844   1.0000
  12.750   1.4236   0.02668   0.02067  -0.0154   0.2718   1.0000
  13.000   1.4215   0.02794   0.02193  -0.0128   0.2596   1.0000
  13.250   1.4193   0.02947   0.02346  -0.0106   0.2479   1.0000
  13.500   1.4147   0.03135   0.02533  -0.0084   0.2348   1.0000
  13.750   1.4101   0.03341   0.02740  -0.0066   0.2221   1.0000
  14.000   1.4076   0.03554   0.02969  -0.0052   0.2025   1.0000
  14.250   1.3931   0.03873   0.03280  -0.0037   0.1705   1.0000
  14.500   1.3696   0.04308   0.03700  -0.0025   0.1513   1.0000
  14.750   1.3531   0.04716   0.04108  -0.0018   0.1388   1.0000
  15.000   1.3354   0.05166   0.04558  -0.0016   0.1268   1.0000
  15.250   1.3164   0.05658   0.05051  -0.0018   0.1159   1.0000
  15.500   1.2948   0.06205   0.05597  -0.0024   0.1042   1.0000
  15.750   1.2824   0.06653   0.06053  -0.0030   0.0961   1.0000
  16.000   1.2652   0.07177   0.06580  -0.0039   0.0873   1.0000
  16.250   1.2463   0.07739   0.07144  -0.0051   0.0776   1.0000
  16.500   1.2273   0.08318   0.07722  -0.0064   0.0670   1.0000
  16.750   1.2077   0.08924   0.08324  -0.0080   0.0545   1.0000
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