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GOE 422 AIRFOIL (goe422-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 422 AIRFOIL (goe422-il)
Reynolds number: 200,000
Max Cl/Cd: 71.01 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe422-il-200000.txt
Download as CSV file: xf-goe422-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 422 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250   0.0499   0.10208   0.09816  -0.1140   0.9437   0.0694
 -10.000   0.0616   0.09895   0.09502  -0.1166   0.9388   0.0715
  -9.750   0.0392   0.09469   0.09077  -0.1234   0.9270   0.0740
  -9.500   0.0606   0.09218   0.08826  -0.1216   0.9220   0.0746
  -9.250   0.0747   0.08998   0.08606  -0.1207   0.9145   0.0754
  -9.000   0.0871   0.08742   0.08347  -0.1212   0.9097   0.0767
  -8.750   0.0919   0.08510   0.08116  -0.1216   0.9004   0.0783
  -8.500   0.0455   0.07925   0.07533  -0.1336   0.8855   0.0820
  -8.250   0.0722   0.07705   0.07312  -0.1296   0.8824   0.0825
  -8.000   0.0911   0.07496   0.07100  -0.1279   0.8785   0.0832
  -7.750   0.1028   0.07299   0.06903  -0.1273   0.8717   0.0842
  -7.500   0.1111   0.07066   0.06669  -0.1277   0.8648   0.0857
  -7.250   0.0691   0.06143   0.05721  -0.1457   0.8515   0.0915
  -7.000   0.0905   0.05955   0.05540  -0.1436   0.8470   0.0920
  -6.750   0.1103   0.05784   0.05368  -0.1424   0.8431   0.0928
  -6.500   0.1226   0.05636   0.05221  -0.1415   0.8357   0.0940
  -6.250   0.1169   0.04966   0.04494  -0.1503   0.8277   0.1022
  -6.000   0.1408   0.04750   0.04287  -0.1499   0.8238   0.1031
  -5.750   0.1545   0.04616   0.04158  -0.1486   0.8160   0.1043
  -5.500   0.1378   0.02910   0.02244  -0.1508   0.8095   0.0661
  -5.250   0.1651   0.02700   0.02001  -0.1512   0.8056   0.0659
  -5.000   0.1815   0.02571   0.01847  -0.1495   0.7977   0.0660
  -4.750   0.2062   0.02432   0.01682  -0.1491   0.7921   0.0670
  -4.500   0.2367   0.02352   0.01598  -0.1497   0.7877   0.0685
  -4.250   0.2595   0.02284   0.01520  -0.1488   0.7812   0.0696
  -4.000   0.2838   0.02199   0.01418  -0.1481   0.7745   0.0707
  -3.750   0.3139   0.02108   0.01303  -0.1482   0.7696   0.0723
  -3.500   0.3412   0.02039   0.01212  -0.1479   0.7639   0.0741
  -3.250   0.3642   0.01987   0.01167  -0.1469   0.7556   0.0762
  -3.000   0.3954   0.01934   0.01103  -0.1472   0.7496   0.0800
  -2.750   0.4199   0.01887   0.01053  -0.1463   0.7418   0.0837
  -2.500   0.4461   0.01846   0.01011  -0.1458   0.7344   0.0883
  -2.250   0.4769   0.01788   0.00948  -0.1461   0.7292   0.0945
  -2.000   0.4996   0.01761   0.00923  -0.1450   0.7217   0.1030
  -1.750   0.5258   0.01717   0.00883  -0.1446   0.7150   0.1149
  -1.500   0.5557   0.01662   0.00831  -0.1449   0.7099   0.1304
  -1.250   0.5775   0.01637   0.00817  -0.1438   0.7020   0.1457
  -1.000   0.6044   0.01603   0.00789  -0.1436   0.6953   0.1645
  -0.750   0.6344   0.01573   0.00760  -0.1439   0.6898   0.1917
  -0.500   0.6555   0.01546   0.00765  -0.1427   0.6812   0.2452
  -0.250   0.6806   0.01473   0.00753  -0.1424   0.6749   0.4224
   0.000   0.6955   0.01390   0.00775  -0.1393   0.6686   0.7418
   0.250   0.7212   0.01364   0.00777  -0.1378   0.6607   0.8929
   0.500   0.7867   0.01352   0.00746  -0.1451   0.6539   1.0000
   0.750   0.8052   0.01365   0.00753  -0.1433   0.6449   1.0000
   1.000   0.8312   0.01368   0.00740  -0.1429   0.6375   1.0000
   1.250   0.8538   0.01381   0.00743  -0.1419   0.6293   1.0000
   1.500   0.8779   0.01390   0.00741  -0.1411   0.6212   1.0000
   1.750   0.9035   0.01403   0.00740  -0.1406   0.6136   1.0000
   2.000   0.9256   0.01417   0.00747  -0.1396   0.6047   1.0000
   2.250   0.9530   0.01429   0.00744  -0.1394   0.5973   1.0000
   2.500   0.9734   0.01447   0.00758  -0.1380   0.5876   1.0000
   2.750   1.0001   0.01461   0.00756  -0.1378   0.5792   1.0000
   3.000   1.0196   0.01479   0.00772  -0.1362   0.5687   1.0000
   3.250   1.0443   0.01498   0.00777  -0.1356   0.5595   1.0000
   3.500   1.0646   0.01519   0.00792  -0.1342   0.5491   1.0000
   3.750   1.0874   0.01542   0.00806  -0.1333   0.5396   1.0000
   4.000   1.1086   0.01566   0.00822  -0.1322   0.5297   1.0000
   4.250   1.1299   0.01594   0.00843  -0.1310   0.5202   1.0000
   4.500   1.1511   0.01621   0.00860  -0.1299   0.5107   1.0000
   4.750   1.1705   0.01653   0.00888  -0.1285   0.5010   1.0000
   5.000   1.1915   0.01683   0.00907  -0.1273   0.4918   1.0000
   5.250   1.2093   0.01717   0.00939  -0.1257   0.4825   1.0000
   5.500   1.2290   0.01749   0.00963  -0.1243   0.4741   1.0000
   5.750   1.2465   0.01786   0.00998  -0.1227   0.4659   1.0000
   6.000   1.2642   0.01823   0.01030  -0.1210   0.4581   1.0000
   6.250   1.2860   0.01863   0.01061  -0.1202   0.4513   1.0000
   6.500   1.3017   0.01905   0.01107  -0.1183   0.4441   1.0000
   6.750   1.3230   0.01945   0.01138  -0.1174   0.4379   1.0000
   7.000   1.3421   0.01990   0.01183  -0.1162   0.4317   1.0000
   7.250   1.3584   0.02036   0.01231  -0.1146   0.4255   1.0000
   7.500   1.3800   0.02078   0.01265  -0.1138   0.4200   1.0000
   7.750   1.3986   0.02127   0.01315  -0.1126   0.4145   1.0000
   8.000   1.4133   0.02179   0.01371  -0.1108   0.4086   1.0000
   8.250   1.4321   0.02225   0.01412  -0.1097   0.4030   1.0000
   8.500   1.4511   0.02277   0.01462  -0.1087   0.3978   1.0000
   8.750   1.4655   0.02335   0.01528  -0.1070   0.3930   1.0000
   9.000   1.4827   0.02389   0.01584  -0.1057   0.3885   1.0000
   9.250   1.5054   0.02435   0.01623  -0.1053   0.3843   1.0000
   9.500   1.5230   0.02495   0.01687  -0.1042   0.3803   1.0000
   9.750   1.5357   0.02564   0.01765  -0.1024   0.3760   1.0000
  10.000   1.5508   0.02626   0.01833  -0.1010   0.3717   1.0000
  10.250   1.5709   0.02678   0.01880  -0.1002   0.3675   1.0000
  10.500   1.5893   0.02740   0.01944  -0.0994   0.3637   1.0000
  10.750   1.5986   0.02826   0.02043  -0.0973   0.3596   1.0000
  11.000   1.6089   0.02907   0.02131  -0.0955   0.3548   1.0000
  11.250   1.6258   0.02967   0.02187  -0.0944   0.3501   1.0000
  11.500   1.6365   0.03057   0.02282  -0.0927   0.3455   1.0000
  11.750   1.6413   0.03170   0.02409  -0.0905   0.3406   1.0000
  12.000   1.6510   0.03265   0.02509  -0.0889   0.3359   1.0000
  12.250   1.6692   0.03324   0.02559  -0.0881   0.3307   1.0000
  12.500   1.6675   0.03484   0.02739  -0.0855   0.3259   1.0000
  12.750   1.6712   0.03621   0.02885  -0.0836   0.3205   1.0000
  13.000   1.6831   0.03713   0.02976  -0.0824   0.3155   1.0000
  13.250   1.6871   0.03864   0.03138  -0.0807   0.3108   1.0000
  13.500   1.6883   0.04040   0.03329  -0.0790   0.3055   1.0000
  13.750   1.6940   0.04185   0.03477  -0.0775   0.3000   1.0000
  14.000   1.6967   0.04363   0.03664  -0.0761   0.2944   1.0000
  14.250   1.6945   0.04592   0.03909  -0.0745   0.2878   1.0000
  14.500   1.6979   0.04771   0.04083  -0.0733   0.2810   1.0000
  14.750   1.6914   0.05067   0.04402  -0.0719   0.2729   1.0000
  15.000   1.6874   0.05338   0.04675  -0.0707   0.2641   1.0000
  15.250   1.6784   0.05686   0.05037  -0.0697   0.2528   1.0000
  15.500   1.6669   0.06076   0.05435  -0.0688   0.2387   1.0000
  15.750   1.6489   0.06551   0.05909  -0.0679   0.2204   1.0000
  16.000   1.6245   0.07115   0.06468  -0.0672   0.1967   1.0000
  16.250   1.5935   0.07777   0.07118  -0.0667   0.1778   1.0000
  16.500   1.5655   0.08421   0.07755  -0.0664   0.1644   1.0000
  16.750   1.5430   0.09006   0.08336  -0.0664   0.1550   1.0000
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