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DEFIANT CANARD BL110 AIRFOIL (defcnd2-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: DEFIANT CANARD BL110 AIRFOIL (defcnd2-il)
Reynolds number: 100,000
Max Cl/Cd: 47.87 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-defcnd2-il-100000-n5.txt
Download as CSV file: xf-defcnd2-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3208   0.09591   0.09130  -0.0540   1.0000   0.0315
 -10.000  -0.3242   0.09369   0.08916  -0.0529   1.0000   0.0313
  -9.750  -0.3351   0.09155   0.08713  -0.0513   1.0000   0.0310
  -9.500  -0.3291   0.08623   0.08183  -0.0560   0.9908   0.0307
  -9.250  -0.3236   0.07963   0.07524  -0.0630   0.9803   0.0303
  -9.000  -0.3230   0.07102   0.06659  -0.0734   0.9690   0.0298
  -8.750  -0.3302   0.06326   0.05867  -0.0819   0.9553   0.0293
  -8.500  -0.3402   0.05729   0.05246  -0.0855   0.9408   0.0293
  -8.250  -0.3467   0.05226   0.04709  -0.0868   0.9278   0.0297
  -8.000  -0.3472   0.04812   0.04259  -0.0868   0.9165   0.0297
  -7.750  -0.3433   0.04406   0.03805  -0.0863   0.9076   0.0302
  -7.500  -0.3379   0.04085   0.03440  -0.0847   0.8973   0.0305
  -7.250  -0.3278   0.03785   0.03095  -0.0833   0.8886   0.0306
  -7.000  -0.3132   0.03517   0.02778  -0.0820   0.8806   0.0308
  -6.750  -0.2979   0.03288   0.02504  -0.0804   0.8720   0.0311
  -6.500  -0.2769   0.03080   0.02251  -0.0794   0.8647   0.0314
  -6.250  -0.2570   0.02902   0.02048  -0.0783   0.8565   0.0320
  -6.000  -0.2329   0.02767   0.01899  -0.0779   0.8496   0.0331
  -5.750  -0.2108   0.02672   0.01790  -0.0770   0.8415   0.0351
  -5.500  -0.1853   0.02557   0.01653  -0.0765   0.8344   0.0371
  -5.250  -0.1612   0.02444   0.01520  -0.0756   0.8263   0.0383
  -5.000  -0.1351   0.02336   0.01395  -0.0750   0.8188   0.0396
  -4.750  -0.1135   0.02240   0.01299  -0.0739   0.8102   0.0413
  -4.500  -0.0888   0.02166   0.01219  -0.0732   0.8025   0.0446
  -4.250  -0.0676   0.02108   0.01150  -0.0718   0.7927   0.0483
  -4.000  -0.0449   0.02032   0.01069  -0.0708   0.7845   0.0526
  -3.750  -0.0240   0.01975   0.01003  -0.0692   0.7742   0.0584
  -3.500  -0.0035   0.01913   0.00941  -0.0677   0.7638   0.0696
  -3.250   0.0187   0.01844   0.00881  -0.0665   0.7546   0.0970
  -3.000   0.0381   0.01784   0.00840  -0.0649   0.7435   0.1459
  -2.750   0.0553   0.01705   0.00810  -0.0632   0.7331   0.2487
  -2.500   0.0661   0.01573   0.00787  -0.0602   0.7239   0.4857
  -2.250   0.0831   0.01528   0.00808  -0.0570   0.7131   0.6837
  -2.000   0.1068   0.01522   0.00806  -0.0554   0.7021   0.7496
  -1.750   0.1352   0.01523   0.00802  -0.0545   0.6918   0.7991
  -1.500   0.1680   0.01529   0.00798  -0.0544   0.6812   0.8378
  -1.250   0.2026   0.01542   0.00798  -0.0549   0.6690   0.8670
  -1.000   0.2415   0.01559   0.00798  -0.0563   0.6571   0.8943
  -0.750   0.2887   0.01581   0.00799  -0.0593   0.6449   0.9169
  -0.500   0.3332   0.01591   0.00787  -0.0622   0.6327   0.9301
  -0.250   0.3698   0.01595   0.00770  -0.0640   0.6205   0.9401
   0.000   0.4084   0.01598   0.00753  -0.0662   0.6075   0.9474
   0.250   0.4422   0.01602   0.00741  -0.0676   0.5947   0.9558
   0.500   0.4785   0.01607   0.00728  -0.0696   0.5817   0.9629
   0.750   0.5120   0.01613   0.00717  -0.0710   0.5692   0.9706
   1.000   0.5476   0.01620   0.00707  -0.0729   0.5571   0.9776
   1.500   0.6173   0.01639   0.00697  -0.0766   0.5348   0.9917
   1.750   0.6531   0.01650   0.00696  -0.0788   0.5246   0.9984
   2.000   0.6750   0.01663   0.00698  -0.0781   0.5163   1.0000
   2.250   0.6909   0.01678   0.00709  -0.0762   0.5076   1.0000
   2.500   0.7080   0.01696   0.00714  -0.0745   0.5002   1.0000
   2.750   0.7239   0.01714   0.00731  -0.0726   0.4913   1.0000
   3.000   0.7415   0.01733   0.00739  -0.0710   0.4841   1.0000
   3.250   0.7581   0.01754   0.00759  -0.0692   0.4760   1.0000
   3.500   0.7766   0.01776   0.00772  -0.0676   0.4699   1.0000
   3.750   0.7944   0.01799   0.00797  -0.0660   0.4631   1.0000
   4.000   0.8134   0.01823   0.00817  -0.0646   0.4574   1.0000
   4.250   0.8330   0.01849   0.00838  -0.0633   0.4524   1.0000
   4.500   0.8520   0.01877   0.00867  -0.0619   0.4468   1.0000
   4.750   0.8720   0.01904   0.00892  -0.0606   0.4420   1.0000
   5.000   0.8923   0.01933   0.00919  -0.0594   0.4375   1.0000
   5.250   0.9116   0.01965   0.00954  -0.0581   0.4325   1.0000
   5.500   0.9318   0.01995   0.00984  -0.0569   0.4281   1.0000
   5.750   0.9533   0.02026   0.01012  -0.0559   0.4243   1.0000
   6.000   0.9721   0.02063   0.01057  -0.0546   0.4195   1.0000
   6.250   0.9920   0.02098   0.01095  -0.0534   0.4152   1.0000
   6.500   1.0135   0.02131   0.01130  -0.0525   0.4115   1.0000
   6.750   1.0337   0.02170   0.01173  -0.0514   0.4076   1.0000
   7.000   1.0528   0.02213   0.01224  -0.0502   0.4033   1.0000
   7.250   1.0734   0.02252   0.01267  -0.0492   0.3994   1.0000
   7.500   1.0962   0.02290   0.01307  -0.0485   0.3961   1.0000
   7.750   1.1147   0.02340   0.01367  -0.0473   0.3921   1.0000
   8.000   1.1332   0.02389   0.01427  -0.0460   0.3879   1.0000
   8.250   1.1544   0.02433   0.01475  -0.0452   0.3840   1.0000
   8.750   1.1934   0.02538   0.01601  -0.0431   0.3765   1.0000
   9.000   1.2114   0.02596   0.01672  -0.0418   0.3727   1.0000
   9.250   1.2328   0.02650   0.01734  -0.0411   0.3693   1.0000
   9.500   1.2586   0.02702   0.01791  -0.0411   0.3665   1.0000
   9.750   1.2725   0.02778   0.01886  -0.0394   0.3630   1.0000
  10.000   1.2856   0.02853   0.01980  -0.0375   0.3591   1.0000
  10.250   1.3043   0.02901   0.02035  -0.0364   0.3540   1.0000
  10.500   1.3178   0.02952   0.02096  -0.0345   0.3478   1.0000
  10.750   1.3208   0.03013   0.02171  -0.0310   0.3411   1.0000
  11.000   1.3414   0.03041   0.02198  -0.0301   0.3349   1.0000
  11.250   1.3326   0.03138   0.02319  -0.0252   0.3291   1.0000
  11.500   1.3418   0.03201   0.02394  -0.0230   0.3236   1.0000
  11.750   1.3508   0.03269   0.02474  -0.0208   0.3185   1.0000
  12.000   1.3430   0.03404   0.02633  -0.0171   0.3129   1.0000
  12.250   1.3503   0.03481   0.02722  -0.0152   0.3075   1.0000
  12.500   1.3432   0.03642   0.02906  -0.0122   0.3018   1.0000
  12.750   1.3375   0.03803   0.03086  -0.0097   0.2955   1.0000
  13.000   1.3332   0.03976   0.03276  -0.0077   0.2894   1.0000
  13.250   1.3236   0.04203   0.03521  -0.0057   0.2826   1.0000
  13.500   1.3167   0.04422   0.03754  -0.0042   0.2754   1.0000
  13.750   1.3137   0.04617   0.03957  -0.0030   0.2671   1.0000
  14.000   1.2992   0.04951   0.04304  -0.0020   0.2585   1.0000
  14.250   1.2936   0.05204   0.04560  -0.0013   0.2482   1.0000
  14.500   1.2858   0.05497   0.04851  -0.0008   0.2363   1.0000
  14.750   1.2639   0.06013   0.05384  -0.0011   0.2277   1.0000
  15.000   1.2444   0.06529   0.05911  -0.0018   0.2179   1.0000
  15.250   1.2214   0.07123   0.06516  -0.0029   0.2070   1.0000
  15.500   1.1790   0.08054   0.07467  -0.0055   0.1966   1.0000
  15.750   1.1512   0.08797   0.08223  -0.0076   0.1852   1.0000
  16.000   1.1620   0.08882   0.08278  -0.0075   0.1598   1.0000
  16.500   1.1417   0.09774   0.09137  -0.0097   0.1307   1.0000
  16.750   1.1294   0.10285   0.09643  -0.0112   0.1187   1.0000
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