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DU86-084/18 8.44% (du8608418-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: DU86-084/18 8.44% (du8608418-il)
Reynolds number: 50,000
Max Cl/Cd: 31.29 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-du8608418-il-50000-n5.txt
Download as CSV file: xf-du8608418-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DU86-084/18 8.44%                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5486   0.10283   0.09627  -0.0170   1.0000   0.0384
  -9.250  -0.5440   0.09406   0.08751  -0.0203   1.0000   0.0372
  -9.000  -0.5443   0.08932   0.08283  -0.0231   1.0000   0.0366
  -8.750  -0.5468   0.08422   0.07778  -0.0268   1.0000   0.0361
  -8.500  -0.5519   0.07925   0.07286  -0.0301   1.0000   0.0357
  -8.250  -0.5588   0.07488   0.06849  -0.0319   1.0000   0.0352
  -8.000  -0.5643   0.07037   0.06393  -0.0335   1.0000   0.0347
  -7.750  -0.5684   0.06607   0.05954  -0.0344   1.0000   0.0342
  -7.500  -0.5716   0.06181   0.05513  -0.0346   1.0000   0.0339
  -7.250  -0.5731   0.05782   0.05093  -0.0341   1.0000   0.0336
  -7.000  -0.5735   0.05412   0.04697  -0.0328   1.0000   0.0334
  -6.750  -0.5735   0.05077   0.04332  -0.0307   1.0000   0.0339
  -6.500  -0.5720   0.04777   0.03998  -0.0282   1.0000   0.0346
  -6.250  -0.5683   0.04484   0.03665  -0.0256   1.0000   0.0357
  -6.000  -0.5615   0.04203   0.03331  -0.0230   1.0000   0.0371
  -5.750  -0.5511   0.03938   0.03010  -0.0205   1.0000   0.0382
  -5.500  -0.5376   0.03672   0.02695  -0.0182   1.0000   0.0389
  -5.250  -0.5222   0.03388   0.02380  -0.0165   1.0000   0.0400
  -5.000  -0.5044   0.03161   0.02125  -0.0148   1.0000   0.0417
  -4.750  -0.4846   0.02968   0.01904  -0.0132   1.0000   0.0439
  -4.500  -0.4635   0.02798   0.01703  -0.0116   1.0000   0.0483
  -4.250  -0.4432   0.02653   0.01543  -0.0102   1.0000   0.0562
  -4.000  -0.4211   0.02521   0.01380  -0.0086   1.0000   0.0642
  -3.750  -0.4001   0.02393   0.01247  -0.0074   1.0000   0.0806
  -3.500  -0.3786   0.02253   0.01112  -0.0062   1.0000   0.1088
  -3.250  -0.3605   0.02081   0.01012  -0.0050   1.0000   0.2120
  -3.000  -0.3495   0.01903   0.00960  -0.0024   1.0000   0.4363
  -2.750  -0.3184   0.01868   0.01078   0.0021   1.0000   0.8802
  -2.500  -0.1406   0.01887   0.00960  -0.0246   1.0000   1.0000
  -2.250  -0.1324   0.01881   0.00931  -0.0218   1.0000   1.0000
  -2.000  -0.1233   0.01878   0.00905  -0.0192   1.0000   1.0000
  -1.750  -0.1135   0.01876   0.00883  -0.0165   1.0000   1.0000
  -1.500  -0.1032   0.01875   0.00865  -0.0140   1.0000   1.0000
  -1.250  -0.0923   0.01876   0.00844  -0.0115   1.0000   1.0000
  -1.000  -0.0811   0.01879   0.00832  -0.0091   1.0000   1.0000
  -0.750  -0.0696   0.01883   0.00823  -0.0067   1.0000   1.0000
  -0.500  -0.0577   0.01889   0.00816  -0.0044   1.0000   1.0000
  -0.250  -0.0318   0.01904   0.00819  -0.0049   0.9957   1.0000
   0.000   0.0006   0.01926   0.00826  -0.0067   0.9890   1.0000
   0.250   0.0354   0.01957   0.00847  -0.0088   0.9824   1.0000
   0.500   0.0679   0.01981   0.00866  -0.0105   0.9745   1.0000
   0.750   0.1044   0.02013   0.00895  -0.0129   0.9670   1.0000
   1.000   0.1404   0.02044   0.00924  -0.0151   0.9584   1.0000
   1.250   0.1758   0.02075   0.00957  -0.0172   0.9491   1.0000
   1.500   0.2168   0.02109   0.00996  -0.0203   0.9400   1.0000
   1.750   0.2583   0.02139   0.01038  -0.0233   0.9296   1.0000
   2.000   0.2992   0.02166   0.01076  -0.0261   0.9175   1.0000
   2.250   0.3450   0.02187   0.01112  -0.0296   0.9044   1.0000
   2.500   0.3907   0.02197   0.01141  -0.0326   0.8892   1.0000
   2.750   0.4316   0.02202   0.01171  -0.0344   0.8714   1.0000
   3.000   0.4665   0.02203   0.01193  -0.0349   0.8515   1.0000
   3.250   0.5011   0.02195   0.01207  -0.0349   0.8313   1.0000
   3.500   0.5252   0.02189   0.01222  -0.0330   0.8082   1.0000
   3.750   0.5326   0.02193   0.01251  -0.0287   0.7786   1.0000
   4.000   0.5413   0.02176   0.01253  -0.0247   0.7440   1.0000
   4.250   0.5563   0.02134   0.01232  -0.0212   0.7044   1.0000
   4.500   0.5792   0.02063   0.01179  -0.0182   0.6533   1.0000
   4.750   0.6106   0.01983   0.01082  -0.0155   0.5687   1.0000
   5.000   0.6301   0.02014   0.01061  -0.0122   0.4650   1.0000
   5.250   0.6421   0.02110   0.01116  -0.0091   0.3779   1.0000
   5.500   0.6536   0.02221   0.01189  -0.0064   0.3078   1.0000
   5.750   0.6664   0.02337   0.01276  -0.0042   0.2519   1.0000
   6.000   0.6810   0.02457   0.01373  -0.0024   0.2075   1.0000
   6.250   0.6979   0.02579   0.01487  -0.0008   0.1725   1.0000
   6.500   0.7156   0.02705   0.01604   0.0005   0.1430   1.0000
   6.750   0.7369   0.02845   0.01749   0.0016   0.1218   1.0000
   7.000   0.7579   0.02986   0.01895   0.0026   0.1033   1.0000
   7.250   0.7787   0.03143   0.02066   0.0036   0.0884   1.0000
   7.500   0.8021   0.03341   0.02286   0.0046   0.0768   1.0000
   7.750   0.8205   0.03521   0.02487   0.0057   0.0646   1.0000
   8.000   0.8410   0.03789   0.02789   0.0068   0.0568   1.0000
   8.250   0.8555   0.03992   0.02991   0.0079   0.0492   1.0000
   8.500   0.8707   0.04336   0.03408   0.0095   0.0449   1.0000
   8.750   0.8816   0.04679   0.03797   0.0111   0.0422   1.0000
   9.000   0.8899   0.04939   0.04075   0.0124   0.0389   1.0000
   9.250   0.8919   0.05295   0.04462   0.0139   0.0368   1.0000
   9.500   0.8868   0.05687   0.04907   0.0158   0.0355   1.0000
   9.750   0.8767   0.06092   0.05352   0.0174   0.0347   1.0000
  10.000   0.8624   0.06468   0.05754   0.0188   0.0344   1.0000
  10.250   0.8452   0.06882   0.06187   0.0193   0.0345   1.0000
  10.500   0.8261   0.07360   0.06681   0.0183   0.0346   1.0000
  10.750   0.8075   0.07900   0.07233   0.0161   0.0351   1.0000
  11.000   0.7914   0.08503   0.07842   0.0127   0.0358   1.0000
  11.250   0.7750   0.09225   0.08567   0.0078   0.0362   1.0000
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