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GOE 217 (MVA MK.12) AIRFOIL (goe217-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 217 (MVA MK.12) AIRFOIL (goe217-il)
Reynolds number: 500,000
Max Cl/Cd: 101.67 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe217-il-500000.txt
Download as CSV file: xf-goe217-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 217 (MVA MK.12) AIRFOIL                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.1680   0.10603   0.10359  -0.0607   0.9656   0.0441
 -11.250  -0.2454   0.05853   0.05559  -0.0984   0.8788   0.0511
 -11.000  -0.2898   0.04968   0.04650  -0.1061   0.8614   0.0511
 -10.750  -0.3240   0.04341   0.03999  -0.1125   0.8427   0.0511
 -10.500  -0.3483   0.03612   0.03209  -0.1331   0.8244   0.0513
 -10.250  -0.3350   0.03251   0.02868  -0.1253   0.8101   0.0522
 -10.000  -0.3173   0.03057   0.02672  -0.1246   0.7934   0.0527
  -9.750  -0.2997   0.02834   0.02439  -0.1268   0.7775   0.0533
  -9.250  -0.2545   0.02179   0.01703  -0.1437   0.7476   0.0581
  -9.000  -0.2315   0.02030   0.01553  -0.1437   0.7341   0.0589
  -8.750  -0.1993   0.01874   0.01336  -0.1500   0.7192   0.0637
  -8.500  -0.1773   0.01707   0.01186  -0.1491   0.7074   0.0648
  -8.250  -0.1511   0.01603   0.01075  -0.1497   0.6943   0.0666
  -8.000  -0.1193   0.02318   0.01689  -0.1567   0.6983   0.0471
  -7.750  -0.0868   0.02221   0.01550  -0.1571   0.6851   0.0413
  -7.250  -0.0325   0.02038   0.01363  -0.1564   0.6589   0.0407
  -7.000  -0.0046   0.01964   0.01282  -0.1562   0.6467   0.0405
  -6.750   0.0241   0.01897   0.01212  -0.1563   0.6345   0.0404
  -6.500   0.0527   0.01842   0.01149  -0.1563   0.6231   0.0404
  -6.250   0.0820   0.01789   0.01093  -0.1564   0.6118   0.0404
  -6.000   0.1118   0.01749   0.01045  -0.1567   0.6012   0.0406
  -5.750   0.1428   0.01713   0.01002  -0.1573   0.5911   0.0409
  -5.500   0.1734   0.01686   0.00963  -0.1578   0.5811   0.0412
  -5.250   0.2032   0.01634   0.00915  -0.1581   0.5727   0.0413
  -5.000   0.2337   0.01590   0.00869  -0.1586   0.5639   0.0416
  -4.750   0.2658   0.01547   0.00825  -0.1596   0.5562   0.0419
  -4.500   0.2990   0.01506   0.00783  -0.1609   0.5490   0.0424
  -4.250   0.3322   0.01473   0.00743  -0.1621   0.5420   0.0429
  -4.000   0.3654   0.01443   0.00708  -0.1634   0.5357   0.0435
  -3.750   0.3989   0.01411   0.00673  -0.1646   0.5300   0.0441
  -3.500   0.4319   0.01385   0.00641  -0.1657   0.5242   0.0447
  -3.250   0.4642   0.01368   0.00615  -0.1666   0.5186   0.0454
  -3.000   0.4964   0.01353   0.00594  -0.1674   0.5137   0.0461
  -2.750   0.5300   0.01320   0.00559  -0.1687   0.5091   0.0476
  -2.500   0.5620   0.01305   0.00539  -0.1694   0.5043   0.0494
  -2.250   0.5932   0.01299   0.00525  -0.1699   0.4996   0.0512
  -2.000   0.6244   0.01298   0.00514  -0.1705   0.4946   0.0540
  -1.750   0.6562   0.01285   0.00503  -0.1710   0.4916   0.0604
  -1.500   0.6934   0.01196   0.00467  -0.1737   0.4880   0.2351
  -1.250   0.7253   0.01175   0.00464  -0.1746   0.4844   0.2924
  -1.000   0.7560   0.01172   0.00469  -0.1750   0.4809   0.3357
  -0.750   0.7859   0.01181   0.00480  -0.1752   0.4773   0.3643
  -0.500   0.8156   0.01201   0.00498  -0.1753   0.4733   0.3844
  -0.250   0.8455   0.01207   0.00510  -0.1754   0.4709   0.3991
   0.000   0.8752   0.01217   0.00522  -0.1755   0.4679   0.4107
   0.250   0.9047   0.01229   0.00534  -0.1755   0.4648   0.4207
   0.500   0.9339   0.01241   0.00545  -0.1755   0.4609   0.4303
   0.750   0.9626   0.01261   0.00561  -0.1754   0.4563   0.4387
   1.000   0.9915   0.01285   0.00579  -0.1753   0.4519   0.4467
   1.250   1.0205   0.01291   0.00592  -0.1753   0.4488   0.4538
   1.500   1.0495   0.01301   0.00605  -0.1753   0.4452   0.4590
   1.750   1.0785   0.01312   0.00614  -0.1752   0.4415   0.4639
   2.000   1.1072   0.01328   0.00624  -0.1752   0.4378   0.4682
   2.250   1.1355   0.01349   0.00640  -0.1751   0.4335   0.4729
   2.500   1.1641   0.01357   0.00654  -0.1750   0.4304   0.4772
   2.750   1.1927   0.01366   0.00667  -0.1750   0.4272   0.4814
   3.000   1.2213   0.01377   0.00679  -0.1749   0.4239   0.4856
   3.250   1.2497   0.01391   0.00691  -0.1749   0.4208   0.4894
   3.500   1.2778   0.01405   0.00703  -0.1748   0.4175   0.4933
   3.750   1.3051   0.01431   0.00726  -0.1746   0.4134   0.4983
   4.000   1.3329   0.01442   0.00746  -0.1744   0.4106   0.5035
   4.250   1.3608   0.01454   0.00762  -0.1742   0.4072   0.5088
   4.500   1.3886   0.01467   0.00776  -0.1741   0.4037   0.5127
   4.750   1.4160   0.01477   0.00787  -0.1739   0.4000   0.5163
   5.000   1.4425   0.01497   0.00804  -0.1736   0.3958   0.5196
   5.250   1.4694   0.01513   0.00825  -0.1733   0.3919   0.5231
   5.500   1.4965   0.01522   0.00841  -0.1731   0.3878   0.5268
   5.750   1.5232   0.01535   0.00856  -0.1728   0.3831   0.5303
   6.000   1.5489   0.01555   0.00872  -0.1724   0.3784   0.5335
   6.250   1.5746   0.01576   0.00893  -0.1720   0.3734   0.5365
   6.500   1.6009   0.01583   0.00909  -0.1717   0.3675   0.5404
   6.750   1.6252   0.01603   0.00929  -0.1710   0.3606   0.5436
   7.000   1.6495   0.01625   0.00953  -0.1704   0.3535   0.5469
   7.250   1.6735   0.01646   0.00975  -0.1697   0.3443   0.5503
   7.500   1.6961   0.01675   0.01002  -0.1688   0.3341   0.5538
   7.750   1.7164   0.01714   0.01034  -0.1676   0.3210   0.5571
   8.000   1.7350   0.01758   0.01074  -0.1661   0.3047   0.5606
   8.250   1.7502   0.01818   0.01128  -0.1641   0.2855   0.5637
   8.500   1.7601   0.01898   0.01198  -0.1613   0.2659   0.5666
   8.750   1.7631   0.01988   0.01280  -0.1572   0.2506   0.5694
   9.000   1.7693   0.02091   0.01378  -0.1540   0.2379   0.5725
   9.250   1.7766   0.02197   0.01479  -0.1512   0.2277   0.5757
   9.500   1.7852   0.02302   0.01583  -0.1488   0.2200   0.5788
   9.750   1.7923   0.02421   0.01703  -0.1464   0.2133   0.5821
  10.000   1.7993   0.02549   0.01833  -0.1441   0.2077   0.5852
  10.250   1.8085   0.02669   0.01960  -0.1423   0.2030   0.5884
  10.500   1.8138   0.02826   0.02118  -0.1403   0.1985   0.5917
  10.750   1.8168   0.03010   0.02303  -0.1383   0.1944   0.5949
  11.000   1.8272   0.03143   0.02443  -0.1371   0.1915   0.5984
  11.250   1.8344   0.03308   0.02614  -0.1357   0.1883   0.6015
  11.500   1.8381   0.03509   0.02822  -0.1343   0.1853   0.6045
  11.750   1.8381   0.03753   0.03069  -0.1329   0.1823   0.6077
  12.000   1.8393   0.03994   0.03316  -0.1317   0.1797   0.6112
  12.250   1.8464   0.04184   0.03516  -0.1308   0.1777   0.6153
  12.500   1.8503   0.04409   0.03748  -0.1299   0.1756   0.6187
  12.750   1.8518   0.04660   0.04006  -0.1291   0.1734   0.6217
  13.000   1.8511   0.04940   0.04293  -0.1282   0.1713   0.6246
  13.250   1.8479   0.05251   0.04609  -0.1274   0.1692   0.6277
  13.500   1.8425   0.05584   0.04946  -0.1265   0.1669   0.6309
  13.750   1.8463   0.05833   0.05205  -0.1260   0.1654   0.6348
  14.000   1.8492   0.06093   0.05474  -0.1256   0.1636   0.6384
  14.250   1.8512   0.06364   0.05754  -0.1252   0.1619   0.6417
  14.500   1.8507   0.06665   0.06063  -0.1248   0.1601   0.6452
  14.750   1.8499   0.06970   0.06373  -0.1245   0.1583   0.6492
  15.000   1.8470   0.07304   0.06711  -0.1242   0.1565   0.6531
  15.250   1.8444   0.07624   0.07032  -0.1238   0.1543   0.6565
  15.500   1.8461   0.07909   0.07328  -0.1237   0.1528   0.6600
  15.750   1.8490   0.08182   0.07611  -0.1236   0.1512   0.6639
  16.000   1.8496   0.08485   0.07923  -0.1236   0.1494   0.6681
  16.250   1.8507   0.08781   0.08225  -0.1236   0.1475   0.6721
  16.500   1.8499   0.09102   0.08552  -0.1238   0.1457   0.6757
  16.750   1.8492   0.09417   0.08870  -0.1239   0.1438   0.6796
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