Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 228 (MVA H.38) AIRFOIL (goe228-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 228 (MVA H.38) AIRFOIL (goe228-il)
Reynolds number: 1,000,000
Max Cl/Cd: 116.19 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe228-il-1000000.txt
Download as CSV file: xf-goe228-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 228 (MVA H.38) AIRFOIL                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -16.250  -0.5486   0.08343   0.08105  -0.1015   0.9924   0.0214
 -16.000  -0.5708   0.07480   0.07226  -0.1085   0.9874   0.0215
 -15.750  -0.5818   0.06799   0.06531  -0.1148   0.9825   0.0217
 -15.500  -0.5912   0.06259   0.05979  -0.1190   0.9735   0.0218
 -15.250  -0.5995   0.05800   0.05508  -0.1222   0.9633   0.0219
 -15.000  -0.6075   0.05393   0.05089  -0.1247   0.9523   0.0220
 -14.750  -0.6262   0.04899   0.04580  -0.1276   0.9396   0.0223
 -14.500  -0.6325   0.04533   0.04205  -0.1300   0.9279   0.0225
 -14.250  -0.6335   0.04218   0.03882  -0.1323   0.9170   0.0227
 -14.000  -0.6312   0.03926   0.03580  -0.1347   0.9059   0.0230
 -13.750  -0.6259   0.03644   0.03291  -0.1374   0.8953   0.0232
 -13.500  -0.6189   0.03377   0.03012  -0.1402   0.8857   0.0234
 -13.250  -0.6108   0.03117   0.02743  -0.1433   0.8758   0.0237
 -13.000  -0.5945   0.02868   0.02482  -0.1475   0.8672   0.0240
 -12.750  -0.5736   0.02638   0.02239  -0.1521   0.8589   0.0243
 -12.500  -0.5485   0.02434   0.02021  -0.1569   0.8521   0.0247
 -12.250  -0.5198   0.02256   0.01831  -0.1615   0.8465   0.0251
 -12.000  -0.4907   0.02134   0.01695  -0.1648   0.8413   0.0255
 -11.750  -0.4626   0.02057   0.01604  -0.1667   0.8361   0.0258
 -11.500  -0.4383   0.01887   0.01428  -0.1690   0.8318   0.0265
 -11.250  -0.4106   0.01811   0.01348  -0.1703   0.8272   0.0270
 -11.000  -0.3825   0.01749   0.01278  -0.1715   0.8226   0.0275
 -10.750  -0.3541   0.01692   0.01214  -0.1725   0.8181   0.0279
 -10.500  -0.3253   0.01635   0.01152  -0.1735   0.8142   0.0285
 -10.250  -0.2964   0.01586   0.01096  -0.1743   0.8098   0.0290
 -10.000  -0.2674   0.01546   0.01048  -0.1751   0.8055   0.0295
  -9.750  -0.2382   0.01513   0.01006  -0.1757   0.8009   0.0298
  -9.500  -0.2096   0.01415   0.00903  -0.1770   0.7971   0.0306
  -9.250  -0.1802   0.01358   0.00843  -0.1779   0.7928   0.0312
  -9.000  -0.1507   0.01318   0.00798  -0.1786   0.7882   0.0318
  -8.750  -0.1212   0.01286   0.00760  -0.1792   0.7834   0.0325
  -8.500  -0.0912   0.01251   0.00722  -0.1799   0.7794   0.0333
  -8.250  -0.0613   0.01218   0.00684  -0.1805   0.7744   0.0339
  -8.000  -0.0316   0.01191   0.00650  -0.1811   0.7693   0.0343
  -7.750  -0.0014   0.01143   0.00595  -0.1819   0.7643   0.0352
  -7.500   0.0289   0.01102   0.00552  -0.1827   0.7589   0.0362
  -7.250   0.0589   0.01075   0.00521  -0.1832   0.7528   0.0372
  -7.000   0.0889   0.01054   0.00494  -0.1838   0.7470   0.0383
  -6.750   0.1192   0.01031   0.00468  -0.1843   0.7402   0.0392
  -6.500   0.1491   0.01006   0.00435  -0.1848   0.7328   0.0404
  -6.250   0.1795   0.00980   0.00407  -0.1854   0.7251   0.0422
  -6.000   0.2092   0.00963   0.00385  -0.1859   0.7160   0.0440
  -5.750   0.2393   0.00945   0.00363  -0.1863   0.7065   0.0465
  -5.500   0.2688   0.00931   0.00344  -0.1867   0.6957   0.0507
  -5.250   0.2985   0.00917   0.00329  -0.1871   0.6831   0.0577
  -5.000   0.3278   0.00907   0.00317  -0.1875   0.6697   0.0666
  -4.750   0.3570   0.00900   0.00304  -0.1878   0.6559   0.0745
  -4.500   0.3859   0.00897   0.00294  -0.1880   0.6422   0.0807
  -4.250   0.4147   0.00894   0.00284  -0.1882   0.6277   0.0870
  -4.000   0.4434   0.00890   0.00276  -0.1885   0.6131   0.0959
  -3.750   0.4726   0.00880   0.00267  -0.1889   0.5992   0.1160
  -3.500   0.5018   0.00863   0.00258  -0.1894   0.5865   0.1590
  -3.250   0.5309   0.00847   0.00252  -0.1899   0.5747   0.2087
  -3.000   0.5598   0.00844   0.00253  -0.1902   0.5633   0.2444
  -2.750   0.5886   0.00848   0.00256  -0.1904   0.5533   0.2641
  -2.250   0.6455   0.00863   0.00265  -0.1907   0.5339   0.2903
  -2.000   0.6735   0.00873   0.00270  -0.1907   0.5244   0.3009
  -1.750   0.7022   0.00881   0.00275  -0.1909   0.5162   0.3094
  -1.500   0.7299   0.00892   0.00281  -0.1909   0.5076   0.3168
  -1.250   0.7588   0.00898   0.00285  -0.1911   0.5010   0.3227
  -1.000   0.7866   0.00910   0.00291  -0.1911   0.4931   0.3277
  -0.750   0.8148   0.00918   0.00296  -0.1912   0.4858   0.3343
  -0.500   0.8427   0.00928   0.00303  -0.1913   0.4780   0.3415
  -0.250   0.8702   0.00940   0.00311  -0.1913   0.4712   0.3467
   0.000   0.8986   0.00946   0.00317  -0.1914   0.4653   0.3533
   0.250   0.9258   0.00959   0.00326  -0.1914   0.4584   0.3596
   0.500   0.9535   0.00970   0.00334  -0.1914   0.4522   0.3660
   0.750   0.9812   0.00978   0.00342  -0.1915   0.4458   0.3758
   1.000   1.0076   0.00994   0.00354  -0.1913   0.4391   0.3842
   1.250   1.0356   0.01000   0.00362  -0.1914   0.4344   0.3927
   1.500   1.0629   0.01011   0.00372  -0.1914   0.4292   0.4009
   1.750   1.0893   0.01025   0.00384  -0.1912   0.4237   0.4101
   2.000   1.1163   0.01035   0.00396  -0.1912   0.4190   0.4212
   2.250   1.1434   0.01044   0.00408  -0.1912   0.4139   0.4359
   2.500   1.1694   0.01057   0.00423  -0.1910   0.4085   0.4552
   3.000   1.2222   0.01079   0.00456  -0.1907   0.4000   0.5123
   3.250   1.2481   0.01093   0.00473  -0.1905   0.3957   0.5375
   3.500   1.2728   0.01111   0.00492  -0.1901   0.3912   0.5562
   3.750   1.2973   0.01131   0.00512  -0.1896   0.3869   0.5713
   4.000   1.3231   0.01143   0.00528  -0.1893   0.3837   0.5835
   4.250   1.3478   0.01160   0.00546  -0.1889   0.3799   0.5943
   4.500   1.3704   0.01181   0.00566  -0.1880   0.3758   0.6048
   4.750   1.3897   0.01206   0.00590  -0.1866   0.3713   0.6135
   5.000   1.4134   0.01220   0.00609  -0.1859   0.3685   0.6223
   5.250   1.4368   0.01239   0.00630  -0.1853   0.3651   0.6301
   5.500   1.4594   0.01262   0.00654  -0.1845   0.3613   0.6382
   5.750   1.4808   0.01292   0.00683  -0.1836   0.3575   0.6457
   6.000   1.5026   0.01319   0.00713  -0.1828   0.3541   0.6543
   6.250   1.5261   0.01339   0.00737  -0.1822   0.3517   0.6631
   6.500   1.5489   0.01362   0.00765  -0.1816   0.3488   0.6725
   6.750   1.5707   0.01390   0.00795  -0.1808   0.3458   0.6817
   7.000   1.5914   0.01423   0.00831  -0.1799   0.3427   0.6926
   7.250   1.6111   0.01461   0.00871  -0.1788   0.3392   0.7056
   7.500   1.6336   0.01485   0.00904  -0.1782   0.3368   0.7248
   7.750   1.6561   0.01507   0.00939  -0.1777   0.3342   0.7630
   8.000   1.6728   0.01508   0.00974  -0.1759   0.3316   1.0000
   8.250   1.6924   0.01551   0.01016  -0.1749   0.3279   1.0000
   8.500   1.7093   0.01607   0.01070  -0.1736   0.3231   1.0000
   8.750   1.7309   0.01641   0.01107  -0.1730   0.3201   1.0000
   9.000   1.7509   0.01683   0.01151  -0.1721   0.3159   1.0000
   9.250   1.7688   0.01736   0.01204  -0.1710   0.3117   1.0000
   9.500   1.7847   0.01802   0.01268  -0.1696   0.3070   1.0000
   9.750   1.8048   0.01845   0.01315  -0.1689   0.3034   1.0000
  10.000   1.8223   0.01903   0.01374  -0.1678   0.2979   1.0000
  10.250   1.8366   0.01981   0.01451  -0.1663   0.2924   1.0000
  10.500   1.8542   0.02041   0.01513  -0.1653   0.2873   1.0000
  10.750   1.8671   0.02131   0.01601  -0.1638   0.2786   1.0000
  11.000   1.8803   0.02221   0.01689  -0.1623   0.2690   1.0000
  11.250   1.8887   0.02344   0.01807  -0.1604   0.2557   1.0000
  11.500   1.8842   0.02557   0.02004  -0.1570   0.2274   1.0000
  11.750   1.8567   0.02948   0.02366  -0.1516   0.1823   1.0000
  12.000   1.8517   0.03193   0.02605  -0.1488   0.1699   1.0000
  12.250   1.8528   0.03399   0.02812  -0.1467   0.1625   1.0000
  12.500   1.8577   0.03581   0.02996  -0.1450   0.1588   1.0000
  12.750   1.8604   0.03784   0.03202  -0.1433   0.1550   1.0000
  13.000   1.8622   0.04002   0.03424  -0.1417   0.1506   1.0000
  13.250   1.8697   0.04174   0.03602  -0.1405   0.1482   1.0000
  13.500   1.8761   0.04360   0.03793  -0.1394   0.1456   1.0000
  13.750   1.8792   0.04579   0.04017  -0.1381   0.1425   1.0000
  14.000   1.8775   0.04851   0.04292  -0.1366   0.1386   1.0000
  14.250   1.8786   0.05105   0.04552  -0.1355   0.1350   1.0000
  14.500   1.8837   0.05318   0.04771  -0.1346   0.1309   1.0000
  14.750   1.8780   0.05654   0.05107  -0.1333   0.1245   1.0000
  15.000   1.8725   0.05990   0.05446  -0.1322   0.1152   1.0000
  15.250   1.8477   0.06560   0.06008  -0.1307   0.0972   1.0000
  15.500   1.8138   0.07260   0.06704  -0.1293   0.0799   1.0000
  15.750   1.7783   0.08002   0.07447  -0.1283   0.0664   1.0000
  16.000   1.7446   0.08745   0.08192  -0.1277   0.0540   1.0000
<< Back to GOE 228 (MVA H.38) AIRFOIL (goe228-il)

Polar data table (+)

Polar graphs


<< Back to GOE 228 (MVA H.38) AIRFOIL (goe228-il)