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DU86-084/18 8.44% (du8608418-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: DU86-084/18 8.44% (du8608418-il)
Reynolds number: 100,000
Max Cl/Cd: 43.77 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-du8608418-il-100000-n5.txt
Download as CSV file: xf-du8608418-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.4476   0.12049   0.11599  -0.0064   1.0000   0.0237
 -11.000  -0.5488   0.12298   0.11814  -0.0010   1.0000   0.0239
 -10.750  -0.5454   0.11865   0.11384  -0.0027   1.0000   0.0222
 -10.500  -0.5436   0.11401   0.10923  -0.0049   1.0000   0.0210
 -10.250  -0.5433   0.10902   0.10429  -0.0074   1.0000   0.0199
  -9.250  -0.5441   0.08690   0.08235  -0.0215   1.0000   0.0168
  -9.000  -0.5470   0.08183   0.07734  -0.0246   1.0000   0.0165
  -8.750  -0.5516   0.07570   0.07125  -0.0299   1.0000   0.0164
  -8.500  -0.5592   0.07016   0.06569  -0.0337   1.0000   0.0163
  -8.250  -0.5683   0.06579   0.06128  -0.0351   1.0000   0.0161
  -8.000  -0.5746   0.06114   0.05651  -0.0361   1.0000   0.0161
  -7.750  -0.5790   0.05707   0.05230  -0.0361   1.0000   0.0159
  -7.500  -0.5834   0.05311   0.04812  -0.0350   1.0000   0.0161
  -7.250  -0.5890   0.04999   0.04477  -0.0324   1.0000   0.0162
  -7.000  -0.5867   0.04695   0.04131  -0.0305   0.9950   0.0168
  -6.750  -0.5801   0.04172   0.03567  -0.0308   0.9869   0.0178
  -6.500  -0.5635   0.03809   0.03155  -0.0310   0.9825   0.0183
  -6.250  -0.5462   0.03469   0.02766  -0.0304   0.9784   0.0186
  -6.000  -0.5249   0.03155   0.02401  -0.0301   0.9750   0.0188
  -5.750  -0.5006   0.02882   0.02080  -0.0299   0.9724   0.0194
  -5.500  -0.4745   0.02645   0.01802  -0.0298   0.9704   0.0202
  -5.250  -0.4476   0.02444   0.01568  -0.0297   0.9685   0.0215
  -5.000  -0.4223   0.02309   0.01405  -0.0292   0.9659   0.0248
  -4.750  -0.3965   0.02172   0.01247  -0.0288   0.9637   0.0276
  -4.500  -0.3723   0.02016   0.01084  -0.0284   0.9615   0.0306
  -4.250  -0.3462   0.01909   0.00958  -0.0281   0.9592   0.0353
  -4.000  -0.3194   0.01812   0.00852  -0.0282   0.9572   0.0463
  -3.750  -0.2924   0.01714   0.00764  -0.0283   0.9554   0.0761
  -3.500  -0.2719   0.01605   0.00704  -0.0275   0.9523   0.1657
  -3.250  -0.2505   0.01504   0.00676  -0.0269   0.9495   0.3239
  -2.750  -0.1963   0.01371   0.00731  -0.0240   0.9472   0.7733
  -2.500  -0.1738   0.01417   0.00761  -0.0219   0.9444   0.8696
  -2.250  -0.1438   0.01447   0.00770  -0.0216   0.9425   0.9068
  -2.000  -0.0995   0.01465   0.00766  -0.0243   0.9422   0.9321
  -1.750  -0.0447   0.01469   0.00745  -0.0294   0.9427   0.9499
  -1.500   0.0120   0.01461   0.00719  -0.0353   0.9431   0.9638
  -1.250   0.0656   0.01447   0.00690  -0.0407   0.9429   0.9754
  -1.000   0.1178   0.01428   0.00658  -0.0460   0.9422   0.9858
  -0.750   0.1672   0.01408   0.00630  -0.0508   0.9403   0.9958
  -0.500   0.2034   0.01401   0.00619  -0.0530   0.9359   1.0000
  -0.250   0.2343   0.01402   0.00616  -0.0540   0.9304   1.0000
   0.000   0.2610   0.01407   0.00619  -0.0540   0.9232   1.0000
   0.250   0.2906   0.01409   0.00620  -0.0544   0.9160   1.0000
   0.500   0.3138   0.01418   0.00629  -0.0536   0.9068   1.0000
   0.750   0.3388   0.01423   0.00636  -0.0530   0.8976   1.0000
   1.000   0.3632   0.01427   0.00643  -0.0520   0.8875   1.0000
   1.250   0.3833   0.01434   0.00652  -0.0501   0.8752   1.0000
   1.500   0.4031   0.01439   0.00661  -0.0481   0.8625   1.0000
   1.750   0.4227   0.01445   0.00670  -0.0460   0.8496   1.0000
   2.000   0.4421   0.01450   0.00684  -0.0439   0.8368   1.0000
   2.250   0.4614   0.01455   0.00695  -0.0418   0.8238   1.0000
   2.500   0.4806   0.01456   0.00705  -0.0396   0.8097   1.0000
   2.750   0.4989   0.01453   0.00713  -0.0375   0.7929   1.0000
   3.000   0.5163   0.01445   0.00720  -0.0354   0.7694   1.0000
   3.250   0.5332   0.01437   0.00730  -0.0334   0.7360   1.0000
   3.500   0.5522   0.01398   0.00704  -0.0308   0.6969   1.0000
   3.750   0.5724   0.01342   0.00630  -0.0275   0.6352   1.0000
   4.000   0.5892   0.01346   0.00589  -0.0240   0.5445   1.0000
   4.250   0.6039   0.01407   0.00605  -0.0212   0.4517   1.0000
   4.500   0.6191   0.01480   0.00640  -0.0190   0.3710   1.0000
   4.750   0.6350   0.01553   0.00682  -0.0170   0.3023   1.0000
   5.000   0.6515   0.01624   0.00736  -0.0153   0.2469   1.0000
   5.250   0.6683   0.01695   0.00790  -0.0135   0.2017   1.0000
   5.500   0.6851   0.01766   0.00847  -0.0118   0.1642   1.0000
   5.750   0.7019   0.01838   0.00911  -0.0101   0.1340   1.0000
   6.000   0.7182   0.01916   0.00983  -0.0083   0.1130   1.0000
   6.250   0.7351   0.01994   0.01061  -0.0066   0.0939   1.0000
   6.500   0.7519   0.02080   0.01148  -0.0050   0.0792   1.0000
   6.750   0.7687   0.02181   0.01255  -0.0032   0.0691   1.0000
   7.000   0.7861   0.02281   0.01368  -0.0018   0.0579   1.0000
   7.250   0.8037   0.02390   0.01481  -0.0005   0.0476   1.0000
   7.500   0.8214   0.02504   0.01604   0.0008   0.0384   1.0000
   7.750   0.8396   0.02648   0.01768   0.0022   0.0315   1.0000
   8.000   0.8555   0.02807   0.01930   0.0034   0.0262   1.0000
   8.250   0.8743   0.03009   0.02166   0.0048   0.0235   1.0000
   8.500   0.8917   0.03244   0.02433   0.0061   0.0212   1.0000
   8.750   0.9073   0.03461   0.02677   0.0074   0.0195   1.0000
   9.000   0.9182   0.03688   0.02919   0.0086   0.0174   1.0000
   9.250   0.9280   0.03966   0.03242   0.0103   0.0159   1.0000
   9.500   0.9336   0.04289   0.03612   0.0121   0.0152   1.0000
   9.750   0.9323   0.04658   0.04036   0.0142   0.0147   1.0000
  10.000   0.9258   0.05012   0.04428   0.0163   0.0145   1.0000
  10.250   0.9127   0.05362   0.04808   0.0186   0.0145   1.0000
  10.500   0.8962   0.05755   0.05226   0.0197   0.0144   1.0000
  10.750   0.8779   0.06199   0.05694   0.0196   0.0144   1.0000
  11.000   0.8595   0.06693   0.06206   0.0181   0.0146   1.0000
  11.250   0.8389   0.07312   0.06833   0.0146   0.0147   1.0000
  11.500   0.8176   0.08116   0.07650   0.0087   0.0150   1.0000
  11.750   0.7981   0.09113   0.08653   0.0012   0.0155   1.0000
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