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GOE 418 AIRFOIL (goe418-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 418 AIRFOIL (goe418-il)
Reynolds number: 200,000
Max Cl/Cd: 75.06 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe418-il-200000.txt
Download as CSV file: xf-goe418-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 418 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2467   0.10052   0.09682  -0.0341   1.0000   0.0864
  -8.750  -0.2807   0.10010   0.09651  -0.0328   1.0000   0.0883
  -8.500  -0.2979   0.09623   0.09270  -0.0393   0.9951   0.0891
  -8.250  -0.2642   0.09252   0.08898  -0.0393   0.9929   0.0897
  -8.000  -0.2345   0.08923   0.08569  -0.0412   0.9883   0.0908
  -7.750  -0.2072   0.08582   0.08228  -0.0455   0.9827   0.0928
  -7.500  -0.2099   0.07730   0.07367  -0.0712   0.9597   0.0983
  -7.250  -0.1804   0.07438   0.07079  -0.0689   0.9565   0.0989
  -7.000  -0.1474   0.07161   0.06802  -0.0696   0.9533   0.0999
  -6.750  -0.1194   0.06868   0.06508  -0.0725   0.9437   0.1016
  -6.500  -0.0889   0.06446   0.06081  -0.0812   0.9334   0.1061
  -6.250  -0.0689   0.05724   0.05339  -0.0947   0.9160   0.1101
  -6.000  -0.0418   0.05509   0.05122  -0.0954   0.9029   0.1114
  -5.750  -0.0204   0.05292   0.04898  -0.0965   0.8856   0.1135
  -5.500  -0.0120   0.04667   0.04224  -0.1050   0.8640   0.1218
  -5.250   0.0069   0.04523   0.04084  -0.1033   0.8472   0.1228
  -5.000   0.0097   0.03519   0.02996  -0.1074   0.8302   0.1096
  -4.750   0.0312   0.03328   0.02795  -0.1068   0.8157   0.1070
  -4.500   0.0497   0.03000   0.02431  -0.1067   0.8030   0.1060
  -4.250   0.0673   0.02673   0.02058  -0.1061   0.7893   0.1058
  -4.000   0.0880   0.02433   0.01759  -0.1054   0.7774   0.1079
  -3.750   0.1111   0.02264   0.01559  -0.1048   0.7668   0.1101
  -3.500   0.1359   0.02212   0.01510  -0.1042   0.7549   0.1120
  -3.250   0.1622   0.02144   0.01425  -0.1037   0.7458   0.1145
  -3.000   0.1866   0.02064   0.01323  -0.1029   0.7343   0.1178
  -2.750   0.2130   0.02011   0.01227  -0.1022   0.7244   0.1207
  -2.500   0.2372   0.01891   0.01102  -0.1016   0.7136   0.1235
  -2.250   0.2638   0.01858   0.01065  -0.1011   0.7046   0.1268
  -2.000   0.2899   0.01819   0.01015  -0.1005   0.6954   0.1305
  -1.500   0.3430   0.01718   0.00885  -0.0994   0.6798   0.1375
  -1.250   0.3700   0.01692   0.00856  -0.0990   0.6723   0.1414
  -1.000   0.3970   0.01671   0.00826  -0.0985   0.6651   0.1454
  -0.750   0.4238   0.01658   0.00802  -0.0980   0.6573   0.1490
  -0.500   0.4511   0.01610   0.00749  -0.0976   0.6508   0.1531
  -0.250   0.4773   0.01592   0.00736  -0.0971   0.6434   0.1572
   0.000   0.5040   0.01578   0.00719  -0.0965   0.6355   0.1616
   0.250   0.5315   0.01573   0.00702  -0.0961   0.6281   0.1654
   0.500   0.5567   0.01541   0.00676  -0.0953   0.6193   0.1698
   0.750   0.5837   0.01528   0.00662  -0.0948   0.6116   0.1746
   1.000   0.6092   0.01519   0.00657  -0.0940   0.6031   0.1794
   1.250   0.6356   0.01513   0.00646  -0.0934   0.5950   0.1844
   1.500   0.6617   0.01499   0.00638  -0.0928   0.5879   0.1910
   1.750   0.6868   0.01491   0.00637  -0.0920   0.5794   0.1981
   2.000   0.7133   0.01483   0.00629  -0.0914   0.5719   0.2078
   2.250   0.7377   0.01476   0.00632  -0.0904   0.5626   0.2220
   2.500   0.7628   0.01460   0.00629  -0.0896   0.5542   0.2499
   2.750   0.7833   0.01396   0.00636  -0.0882   0.5459   0.4502
   3.000   0.8417   0.01299   0.00634  -0.0939   0.5350   1.0000
   3.250   0.8659   0.01314   0.00643  -0.0929   0.5262   1.0000
   3.500   0.8900   0.01325   0.00646  -0.0918   0.5168   1.0000
   3.750   0.9140   0.01340   0.00655  -0.0908   0.5074   1.0000
   4.000   0.9380   0.01353   0.00661  -0.0898   0.4979   1.0000
   4.250   0.9616   0.01368   0.00674  -0.0887   0.4880   1.0000
   4.500   0.9854   0.01383   0.00680  -0.0877   0.4782   1.0000
   4.750   1.0083   0.01399   0.00696  -0.0865   0.4673   1.0000
   5.000   1.0319   0.01417   0.00703  -0.0855   0.4575   1.0000
   5.250   1.0540   0.01432   0.00720  -0.0842   0.4452   1.0000
   5.500   1.0764   0.01452   0.00736  -0.0830   0.4341   1.0000
   5.750   1.0987   0.01474   0.00750  -0.0818   0.4234   1.0000
   6.000   1.1207   0.01497   0.00774  -0.0805   0.4120   1.0000
   6.250   1.1424   0.01523   0.00795  -0.0793   0.4014   1.0000
   6.500   1.1635   0.01550   0.00819  -0.0779   0.3901   1.0000
   6.750   1.1843   0.01579   0.00847  -0.0765   0.3786   1.0000
   7.000   1.2040   0.01613   0.00875  -0.0750   0.3671   1.0000
   7.250   1.2229   0.01648   0.00907  -0.0734   0.3544   1.0000
   7.500   1.2410   0.01684   0.00942  -0.0716   0.3405   1.0000
   7.750   1.2573   0.01726   0.00981  -0.0696   0.3256   1.0000
   8.000   1.2715   0.01774   0.01025  -0.0672   0.3084   1.0000
   8.250   1.2828   0.01830   0.01074  -0.0644   0.2882   1.0000
   8.500   1.2880   0.01898   0.01129  -0.0607   0.2664   1.0000
   8.750   1.2934   0.01973   0.01195  -0.0571   0.2429   1.0000
   9.000   1.2980   0.02062   0.01272  -0.0537   0.2247   1.0000
   9.250   1.3042   0.02154   0.01356  -0.0507   0.2122   1.0000
   9.750   1.3201   0.02345   0.01536  -0.0457   0.1960   1.0000
  10.000   1.3275   0.02452   0.01636  -0.0433   0.1902   1.0000
  10.250   1.3379   0.02550   0.01734  -0.0414   0.1856   1.0000
  10.500   1.3490   0.02645   0.01832  -0.0397   0.1811   1.0000
  10.750   1.3584   0.02756   0.01939  -0.0379   0.1770   1.0000
  11.000   1.3688   0.02871   0.02048  -0.0363   0.1734   1.0000
  11.250   1.3811   0.02968   0.02155  -0.0349   0.1702   1.0000
  11.500   1.3929   0.03073   0.02264  -0.0336   0.1671   1.0000
  11.750   1.4043   0.03183   0.02376  -0.0323   0.1643   1.0000
  12.000   1.4166   0.03301   0.02484  -0.0310   0.1608   1.0000
  12.250   1.4281   0.03416   0.02607  -0.0298   0.1580   1.0000
  12.500   1.4381   0.03538   0.02738  -0.0287   0.1551   1.0000
  12.750   1.4482   0.03663   0.02869  -0.0276   0.1521   1.0000
  13.000   1.4594   0.03787   0.02994  -0.0266   0.1495   1.0000
  13.250   1.4786   0.03881   0.03075  -0.0258   0.1462   1.0000
  13.500   1.4848   0.04032   0.03244  -0.0247   0.1444   1.0000
  13.750   1.4918   0.04186   0.03411  -0.0238   0.1420   1.0000
  14.000   1.4995   0.04339   0.03572  -0.0229   0.1393   1.0000
  14.250   1.5083   0.04487   0.03722  -0.0222   0.1364   1.0000
  14.500   1.5262   0.04589   0.03814  -0.0214   0.1329   1.0000
  14.750   1.5243   0.04815   0.04061  -0.0207   0.1307   1.0000
  15.000   1.5251   0.05033   0.04294  -0.0202   0.1278   1.0000
  15.250   1.5288   0.05232   0.04498  -0.0197   0.1246   1.0000
  15.500   1.5442   0.05344   0.04597  -0.0190   0.1206   1.0000
  15.750   1.5353   0.05665   0.04945  -0.0190   0.1182   1.0000
  16.000   1.5316   0.05956   0.05252  -0.0190   0.1148   1.0000
  16.250   1.5329   0.06200   0.05497  -0.0190   0.1113   1.0000
  16.500   1.5316   0.06485   0.05788  -0.0191   0.1074   1.0000
  16.750   1.5216   0.06884   0.06208  -0.0199   0.1036   1.0000
  17.000   1.5192   0.07196   0.06520  -0.0205   0.0998   1.0000
  17.250   1.5110   0.07602   0.06940  -0.0214   0.0958   1.0000
  17.500   1.5022   0.08035   0.07387  -0.0228   0.0918   1.0000
  17.750   1.5018   0.08345   0.07690  -0.0236   0.0885   1.0000
  18.000   1.4884   0.08881   0.08253  -0.0255   0.0847   1.0000
  18.250   1.4838   0.09283   0.08662  -0.0269   0.0818   1.0000
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