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E224 (10.17%) (e224-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: E224 (10.17%) (e224-il)
Reynolds number: 100,000
Max Cl/Cd: 50.22 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e224-il-100000-n5.txt
Download as CSV file: xf-e224-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E224  (10.17%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5448   0.07637   0.07133  -0.0399   1.0000   0.0189
  -9.750  -0.5553   0.07002   0.06500  -0.0442   1.0000   0.0186
  -9.500  -0.5741   0.06286   0.05780  -0.0502   1.0000   0.0184
  -9.250  -0.5895   0.05847   0.05338  -0.0527   1.0000   0.0180
  -9.000  -0.6098   0.05464   0.04943  -0.0529   1.0000   0.0179
  -8.750  -0.6251   0.05058   0.04515  -0.0524   1.0000   0.0180
  -8.500  -0.6344   0.04677   0.04102  -0.0512   1.0000   0.0182
  -8.250  -0.6378   0.04323   0.03709  -0.0497   1.0000   0.0185
  -7.750  -0.6307   0.03706   0.03024  -0.0464   1.0000   0.0196
  -7.500  -0.6207   0.03471   0.02763  -0.0448   1.0000   0.0201
  -7.250  -0.6087   0.03235   0.02497  -0.0432   1.0000   0.0206
  -7.000  -0.5947   0.03022   0.02255  -0.0416   1.0000   0.0212
  -6.750  -0.5789   0.02830   0.02032  -0.0400   1.0000   0.0219
  -6.500  -0.5621   0.02654   0.01830  -0.0384   1.0000   0.0230
  -6.250  -0.5444   0.02497   0.01651  -0.0368   1.0000   0.0242
  -6.000  -0.5262   0.02362   0.01497  -0.0353   1.0000   0.0262
  -5.750  -0.5088   0.02245   0.01378  -0.0341   1.0000   0.0296
  -5.500  -0.4900   0.02142   0.01262  -0.0327   1.0000   0.0335
  -5.250  -0.4714   0.02023   0.01133  -0.0314   1.0000   0.0381
  -5.000  -0.4515   0.01947   0.01045  -0.0303   1.0000   0.0474
  -4.750  -0.4305   0.01852   0.00955  -0.0296   0.9996   0.0622
  -4.500  -0.3958   0.01754   0.00868  -0.0316   0.9945   0.0935
  -4.250  -0.3621   0.01671   0.00807  -0.0335   0.9887   0.1447
  -4.000  -0.3267   0.01608   0.00766  -0.0357   0.9833   0.2104
  -3.750  -0.2942   0.01554   0.00731  -0.0372   0.9763   0.2752
  -3.500  -0.2583   0.01514   0.00706  -0.0392   0.9705   0.3384
  -3.250  -0.2265   0.01478   0.00684  -0.0402   0.9627   0.3959
  -3.000  -0.1907   0.01448   0.00668  -0.0419   0.9568   0.4542
  -2.750  -0.1597   0.01422   0.00651  -0.0425   0.9485   0.5063
  -2.500  -0.1234   0.01400   0.00639  -0.0441   0.9427   0.5585
  -2.250  -0.0927   0.01381   0.00629  -0.0445   0.9340   0.6048
  -2.000  -0.0563   0.01363   0.00617  -0.0458   0.9283   0.6512
  -1.750  -0.0272   0.01350   0.00609  -0.0457   0.9187   0.6918
  -1.500   0.0056   0.01336   0.00600  -0.0461   0.9112   0.7319
  -1.250   0.0360   0.01325   0.00593  -0.0460   0.9020   0.7698
  -1.000   0.0651   0.01315   0.00585  -0.0456   0.8921   0.8048
  -0.750   0.0978   0.01304   0.00574  -0.0459   0.8839   0.8387
  -0.500   0.1285   0.01296   0.00566  -0.0458   0.8733   0.8709
  -0.250   0.1627   0.01288   0.00556  -0.0466   0.8627   0.9012
   0.000   0.2029   0.01278   0.00543  -0.0486   0.8528   0.9288
   0.250   0.2482   0.01266   0.00526  -0.0517   0.8427   0.9518
   0.500   0.2929   0.01257   0.00512  -0.0550   0.8299   0.9732
   0.750   0.3384   0.01246   0.00497  -0.0585   0.8162   0.9924
   1.000   0.3702   0.01242   0.00487  -0.0593   0.8010   1.0000
   1.250   0.3943   0.01242   0.00481  -0.0585   0.7847   1.0000
   1.500   0.4176   0.01246   0.00480  -0.0576   0.7673   1.0000
   1.750   0.4418   0.01252   0.00479  -0.0567   0.7497   1.0000
   2.000   0.4666   0.01259   0.00482  -0.0559   0.7319   1.0000
   2.250   0.4917   0.01267   0.00484  -0.0552   0.7138   1.0000
   2.500   0.5159   0.01279   0.00492  -0.0543   0.6939   1.0000
   2.750   0.5407   0.01291   0.00502  -0.0535   0.6741   1.0000
   3.000   0.5654   0.01306   0.00512  -0.0527   0.6532   1.0000
   3.250   0.5900   0.01323   0.00525  -0.0519   0.6316   1.0000
   3.500   0.6143   0.01342   0.00540  -0.0510   0.6088   1.0000
   3.750   0.6387   0.01363   0.00558  -0.0502   0.5854   1.0000
   4.000   0.6627   0.01387   0.00579  -0.0493   0.5605   1.0000
   4.250   0.6865   0.01413   0.00601  -0.0484   0.5345   1.0000
   4.500   0.7100   0.01442   0.00626  -0.0474   0.5073   1.0000
   4.750   0.7331   0.01474   0.00656  -0.0465   0.4788   1.0000
   5.000   0.7560   0.01510   0.00687  -0.0455   0.4493   1.0000
   5.250   0.7784   0.01550   0.00721  -0.0444   0.4186   1.0000
   5.500   0.8003   0.01595   0.00759  -0.0434   0.3871   1.0000
   5.750   0.8220   0.01644   0.00802  -0.0423   0.3536   1.0000
   6.000   0.8430   0.01698   0.00852  -0.0412   0.3196   1.0000
   6.250   0.8636   0.01759   0.00904  -0.0401   0.2854   1.0000
   6.500   0.8838   0.01825   0.00962  -0.0390   0.2508   1.0000
   6.750   0.9034   0.01898   0.01026  -0.0378   0.2185   1.0000
   7.000   0.9228   0.01976   0.01098  -0.0367   0.1876   1.0000
   7.250   0.9414   0.02064   0.01176  -0.0355   0.1558   1.0000
   7.500   0.9591   0.02161   0.01261  -0.0343   0.1260   1.0000
   7.750   0.9765   0.02263   0.01358  -0.0330   0.1011   1.0000
   8.000   0.9927   0.02376   0.01461  -0.0316   0.0821   1.0000
   8.250   1.0089   0.02488   0.01576  -0.0302   0.0667   1.0000
   8.500   1.0228   0.02619   0.01706  -0.0285   0.0569   1.0000
   8.750   1.0370   0.02746   0.01848  -0.0267   0.0496   1.0000
   9.000   1.0482   0.02896   0.02003  -0.0247   0.0445   1.0000
   9.250   1.0615   0.03025   0.02146  -0.0229   0.0394   1.0000
   9.500   1.0706   0.03183   0.02311  -0.0209   0.0362   1.0000
   9.750   1.0807   0.03348   0.02492  -0.0188   0.0342   1.0000
  10.000   1.0918   0.03519   0.02683  -0.0168   0.0321   1.0000
  10.250   1.1013   0.03684   0.02864  -0.0150   0.0298   1.0000
  10.500   1.1078   0.03844   0.03032  -0.0131   0.0277   1.0000
  10.750   1.1131   0.04080   0.03275  -0.0113   0.0261   1.0000
  11.000   1.1209   0.04306   0.03532  -0.0097   0.0251   1.0000
  11.250   1.1250   0.04553   0.03808  -0.0080   0.0238   1.0000
  11.500   1.1260   0.04803   0.04085  -0.0065   0.0226   1.0000
  11.750   1.1246   0.05057   0.04361  -0.0053   0.0215   1.0000
  12.000   1.1217   0.05319   0.04639  -0.0045   0.0206   1.0000
  12.250   1.1174   0.05614   0.04952  -0.0041   0.0198   1.0000
  12.500   1.1112   0.05969   0.05323  -0.0041   0.0193   1.0000
  12.750   1.1020   0.06389   0.05763  -0.0047   0.0190   1.0000
  13.000   1.0894   0.06882   0.06278  -0.0058   0.0188   1.0000
  13.250   1.0743   0.07428   0.06846  -0.0079   0.0187   1.0000
  13.500   1.0592   0.08011   0.07452  -0.0107   0.0187   1.0000
  13.750   1.0409   0.08689   0.08151  -0.0145   0.0186   1.0000
  14.000   1.0221   0.09433   0.08915  -0.0190   0.0187   1.0000
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