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DU86-084/18 8.44% (du8608418-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: DU86-084/18 8.44% (du8608418-il)
Reynolds number: 1,000,000
Max Cl/Cd: 71.05 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-du8608418-il-1000000.txt
Download as CSV file: xf-du8608418-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4555   0.08221   0.08032  -0.0171   0.8576   0.0089
  -9.250  -0.4601   0.07617   0.07430  -0.0197   0.8574   0.0089
  -8.000  -0.5648   0.05537   0.05320  -0.0390   0.8556   0.0088
  -7.750  -0.5671   0.05043   0.04811  -0.0386   0.8552   0.0089
  -7.500  -0.5662   0.04606   0.04355  -0.0377   0.8547   0.0089
  -7.250  -0.5626   0.04197   0.03923  -0.0364   0.8539   0.0089
  -7.000  -0.5560   0.03819   0.03519  -0.0350   0.8533   0.0089
  -6.750  -0.5461   0.03476   0.03149  -0.0336   0.8528   0.0090
  -6.500  -0.5656   0.02014   0.01553  -0.0273   0.8517   0.0056
  -6.250  -0.5420   0.01887   0.01406  -0.0266   0.8511   0.0054
  -6.000  -0.5196   0.01691   0.01183  -0.0256   0.8506   0.0054
  -5.750  -0.4995   0.01404   0.00862  -0.0242   0.8501   0.0058
  -5.500  -0.4745   0.01328   0.00778  -0.0239   0.8495   0.0065
  -5.250  -0.4486   0.01276   0.00720  -0.0236   0.8489   0.0071
  -5.000  -0.4228   0.01220   0.00658  -0.0233   0.8483   0.0076
  -4.750  -0.3972   0.01159   0.00589  -0.0229   0.8476   0.0080
  -4.500  -0.3711   0.01117   0.00540  -0.0226   0.8469   0.0084
  -4.250  -0.3442   0.01102   0.00523  -0.0225   0.8460   0.0089
  -4.000  -0.3193   0.01011   0.00416  -0.0219   0.8452   0.0103
  -3.750  -0.2924   0.00971   0.00372  -0.0217   0.8445   0.0129
  -3.500  -0.2654   0.00934   0.00335  -0.0215   0.8435   0.0215
  -3.250  -0.2386   0.00899   0.00311  -0.0214   0.8423   0.0485
  -3.000  -0.2126   0.00856   0.00292  -0.0213   0.8407   0.1037
  -2.750  -0.1867   0.00815   0.00276  -0.0211   0.8386   0.1732
  -2.500  -0.1613   0.00772   0.00262  -0.0209   0.8363   0.2585
  -2.250  -0.1364   0.00733   0.00256  -0.0205   0.8338   0.3590
  -2.000  -0.1107   0.00698   0.00250  -0.0203   0.8313   0.4458
  -1.750  -0.0850   0.00654   0.00238  -0.0201   0.8285   0.5408
  -1.500  -0.0612   0.00593   0.00225  -0.0195   0.8256   0.6820
  -1.250  -0.0414   0.00562   0.00251  -0.0173   0.8230   0.8580
  -1.000  -0.0147   0.00580   0.00265  -0.0168   0.8202   0.8763
  -0.750   0.0123   0.00583   0.00267  -0.0164   0.8170   0.8855
  -0.500   0.0387   0.00586   0.00269  -0.0158   0.8132   0.8933
  -0.250   0.0653   0.00589   0.00269  -0.0153   0.8095   0.9002
   0.000   0.0913   0.00594   0.00272  -0.0146   0.8063   0.9055
   0.250   0.1178   0.00589   0.00269  -0.0141   0.8022   0.9103
   0.500   0.1451   0.00587   0.00265  -0.0138   0.7984   0.9152
   0.750   0.1709   0.00581   0.00257  -0.0131   0.7953   0.9188
   1.000   0.1972   0.00575   0.00253  -0.0125   0.7912   0.9226
   1.250   0.2240   0.00567   0.00248  -0.0121   0.7861   0.9270
   1.500   0.2498   0.00553   0.00232  -0.0114   0.7813   0.9312
   1.750   0.2743   0.00542   0.00228  -0.0104   0.7731   0.9359
   2.000   0.3002   0.00532   0.00221  -0.0098   0.7610   0.9409
   2.250   0.3241   0.00510   0.00198  -0.0085   0.7374   0.9457
   2.500   0.3437   0.00512   0.00175  -0.0063   0.6751   0.9515
   2.750   0.3637   0.00554   0.00185  -0.0047   0.5923   0.9559
   3.000   0.3851   0.00587   0.00191  -0.0035   0.5171   0.9586
   3.250   0.4096   0.00619   0.00202  -0.0030   0.4559   0.9595
   3.500   0.4336   0.00658   0.00214  -0.0026   0.3867   0.9605
   3.750   0.4583   0.00697   0.00228  -0.0023   0.3224   0.9612
   4.000   0.4835   0.00733   0.00244  -0.0022   0.2683   0.9618
   4.250   0.5095   0.00763   0.00259  -0.0021   0.2280   0.9624
   4.500   0.5352   0.00794   0.00276  -0.0020   0.1919   0.9631
   4.750   0.5611   0.00825   0.00293  -0.0019   0.1580   0.9639
   5.000   0.5874   0.00854   0.00314  -0.0019   0.1314   0.9644
   5.250   0.6137   0.00885   0.00335  -0.0019   0.1070   0.9649
   5.500   0.6396   0.00920   0.00359  -0.0019   0.0817   0.9654
   5.750   0.6656   0.00955   0.00384  -0.0019   0.0621   0.9660
   6.000   0.6918   0.00988   0.00412  -0.0019   0.0480   0.9665
   6.250   0.7182   0.01018   0.00438  -0.0019   0.0386   0.9670
   6.500   0.7446   0.01048   0.00470  -0.0019   0.0315   0.9675
   6.750   0.7701   0.01086   0.00503  -0.0018   0.0231   0.9683
   7.000   0.7954   0.01128   0.00542  -0.0017   0.0137   0.9690
   7.250   0.8198   0.01193   0.00608  -0.0013   0.0083   0.9698
   7.500   0.8448   0.01243   0.00663  -0.0011   0.0068   0.9707
   7.750   0.8678   0.01324   0.00755  -0.0005   0.0056   0.9719
   8.000   0.8894   0.01421   0.00867   0.0002   0.0051   0.9732
   8.250   0.9134   0.01481   0.00938   0.0005   0.0049   0.9745
   8.500   0.9365   0.01555   0.01023   0.0010   0.0047   0.9759
   8.750   0.9585   0.01647   0.01128   0.0016   0.0046   0.9776
   9.000   0.9809   0.01737   0.01229   0.0020   0.0043   0.9795
   9.250   1.0037   0.01824   0.01328   0.0023   0.0041   0.9815
   9.500   1.0265   0.01937   0.01454   0.0024   0.0039   0.9841
   9.750   1.0506   0.02031   0.01558   0.0022   0.0036   0.9873
  10.000   1.0733   0.02143   0.01681   0.0020   0.0032   0.9925
  10.250   1.0809   0.02440   0.02010   0.0038   0.0030   1.0000
  10.500   1.0816   0.02801   0.02410   0.0062   0.0029   1.0000
  10.750   1.0670   0.03264   0.02921   0.0100   0.0028   1.0000
  11.000   1.0711   0.03401   0.03075   0.0121   0.0028   1.0000
  11.250   1.0581   0.03708   0.03406   0.0148   0.0028   1.0000
  11.500   1.0465   0.04018   0.03737   0.0166   0.0028   1.0000
  11.750   1.0371   0.04323   0.04060   0.0177   0.0027   1.0000
  12.250   0.9908   0.05375   0.05151   0.0167   0.0028   1.0000
  12.500   0.9848   0.05783   0.05570   0.0145   0.0029   1.0000
  12.750   0.9651   0.06534   0.06337   0.0094   0.0029   1.0000
  13.000   0.9483   0.07427   0.07245   0.0026   0.0029   1.0000
  13.250   0.9384   0.08273   0.08101  -0.0035   0.0029   1.0000
  13.500   0.9313   0.09043   0.08877  -0.0084   0.0029   1.0000
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