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GOE 217 (MVA MK.12) AIRFOIL (goe217-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 217 (MVA MK.12) AIRFOIL (goe217-il)
Reynolds number: 100,000
Max Cl/Cd: 40.18 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe217-il-100000.txt
Download as CSV file: xf-goe217-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.0776   0.11308   0.10856  -0.0609   0.9639   0.1841
  -9.250  -0.0374   0.10808   0.10354  -0.0639   0.9536   0.1868
  -9.000  -0.2557   0.06097   0.05596  -0.1114   0.9295   0.1016
  -8.750  -0.2445   0.04433   0.03793  -0.1465   0.9123   0.0926
  -8.500  -0.2110   0.04098   0.03435  -0.1507   0.8993   0.0919
  -8.250  -0.1730   0.03790   0.03095  -0.1553   0.8880   0.0915
  -8.000  -0.1358   0.03537   0.02813  -0.1586   0.8761   0.0908
  -7.750  -0.1049   0.03353   0.02605  -0.1599   0.8611   0.0899
  -7.500  -0.0701   0.03180   0.02407  -0.1613   0.8499   0.0892
  -7.250  -0.0419   0.03057   0.02267  -0.1614   0.8343   0.0887
  -7.000  -0.0137   0.02954   0.02149  -0.1612   0.8200   0.0885
  -6.750   0.0155   0.02857   0.02038  -0.1606   0.8081   0.0885
  -6.500   0.0405   0.02792   0.01970  -0.1595   0.7930   0.0888
  -6.250   0.0672   0.02731   0.01902  -0.1582   0.7817   0.0893
  -6.000   0.0916   0.02691   0.01863  -0.1567   0.7684   0.0899
  -5.750   0.1173   0.02660   0.01830  -0.1553   0.7579   0.0910
  -5.500   0.1434   0.02638   0.01803  -0.1543   0.7459   0.0928
  -5.250   0.1680   0.02620   0.01796  -0.1527   0.7364   0.0951
  -5.000   0.1960   0.02597   0.01776  -0.1526   0.7247   0.0977
  -4.750   0.2299   0.02553   0.01716  -0.1538   0.7165   0.1005
  -4.500   0.2645   0.02495   0.01660  -0.1564   0.7051   0.1040
  -4.250   0.3035   0.02418   0.01568  -0.1595   0.6969   0.1106
  -4.000   0.3493   0.02271   0.01471  -0.1658   0.6884   0.1838
  -3.750   0.3852   0.02243   0.01461  -0.1681   0.6796   0.2618
  -3.500   0.4187   0.02258   0.01475  -0.1689   0.6728   0.3078
  -3.250   0.4472   0.02324   0.01544  -0.1687   0.6650   0.3371
  -3.000   0.4741   0.02398   0.01617  -0.1678   0.6572   0.3570
  -2.750   0.5003   0.02481   0.01695  -0.1664   0.6514   0.3719
  -2.500   0.5276   0.02564   0.01769  -0.1655   0.6460   0.3867
  -2.250   0.5465   0.02696   0.01919  -0.1626   0.6392   0.3957
  -2.000   0.5718   0.02779   0.01999  -0.1614   0.6335   0.4080
  -1.750   0.5922   0.02889   0.02112  -0.1583   0.6289   0.4147
  -1.500   0.6215   0.02944   0.02154  -0.1582   0.6243   0.4281
  -1.250   0.6349   0.03088   0.02320  -0.1541   0.6181   0.4333
  -1.000   0.6622   0.03151   0.02379  -0.1539   0.6126   0.4491
  -0.750   0.6775   0.03262   0.02497  -0.1497   0.6086   0.4540
  -0.500   0.7177   0.03235   0.02447  -0.1531   0.6049   0.4701
  -0.250   0.7369   0.03308   0.02529  -0.1510   0.6009   0.4737
   0.000   0.7573   0.03378   0.02611  -0.1499   0.5955   0.4802
   0.250   0.7906   0.03387   0.02611  -0.1520   0.5905   0.4940
   0.500   0.8125   0.03431   0.02657  -0.1502   0.5866   0.4998
   0.750   0.8498   0.03435   0.02644  -0.1527   0.5833   0.5151
   1.000   0.8700   0.03501   0.02714  -0.1508   0.5802   0.5203
   1.250   0.8873   0.03612   0.02843  -0.1502   0.5748   0.5289
   1.500   0.9128   0.03673   0.02905  -0.1507   0.5698   0.5395
   1.750   0.9352   0.03720   0.02954  -0.1495   0.5660   0.5473
   2.000   0.9694   0.03739   0.02963  -0.1511   0.5627   0.5598
   2.250   0.9956   0.03758   0.02978  -0.1500   0.5598   0.5673
   2.500   1.0070   0.03946   0.03185  -0.1497   0.5528   0.5768
   2.750   1.0275   0.03978   0.03222  -0.1485   0.5464   0.5841
   3.000   1.0663   0.03890   0.03117  -0.1492   0.5412   0.5959
   3.250   1.0981   0.03855   0.03072  -0.1491   0.5361   0.6052
   3.500   1.1039   0.04018   0.03258  -0.1472   0.5279   0.6122
   3.750   1.1368   0.04000   0.03233  -0.1479   0.5226   0.6218
   4.000   1.1718   0.03939   0.03162  -0.1482   0.5186   0.6307
   4.250   1.1994   0.04003   0.03223  -0.1490   0.5134   0.6385
   4.500   1.2013   0.04173   0.03418  -0.1464   0.5057   0.6429
   4.750   1.2356   0.04132   0.03371  -0.1471   0.5007   0.6509
   5.000   1.2785   0.04040   0.03263  -0.1487   0.4967   0.6583
   5.250   1.2879   0.04178   0.03416  -0.1469   0.4900   0.6630
   5.500   1.3022   0.04279   0.03527  -0.1458   0.4826   0.6688
   5.750   1.3437   0.04176   0.03413  -0.1471   0.4778   0.6759
   6.000   1.3923   0.04049   0.03265  -0.1493   0.4739   0.6828
   6.250   1.3780   0.04322   0.03573  -0.1451   0.4640   0.6858
   6.500   1.4160   0.04231   0.03474  -0.1460   0.4582   0.6924
   6.750   1.4679   0.04068   0.03289  -0.1484   0.4538   0.7005
   7.000   1.4579   0.04292   0.03542  -0.1445   0.4440   0.7036
   7.250   1.4955   0.04194   0.03437  -0.1453   0.4376   0.7090
   7.500   1.5511   0.04017   0.03232  -0.1482   0.4326   0.7173
   7.750   1.5347   0.04233   0.03482  -0.1431   0.4217   0.7206
   8.000   1.5842   0.04057   0.03288  -0.1452   0.4154   0.7280
   8.250   1.5845   0.04176   0.03423  -0.1419   0.4057   0.7320
   8.500   1.6186   0.04098   0.03333  -0.1424   0.3976   0.7380
   8.750   1.6326   0.04128   0.03368  -0.1405   0.3887   0.7432
   9.000   1.6502   0.04122   0.03359  -0.1389   0.3795   0.7497
   9.250   1.6662   0.04147   0.03381  -0.1373   0.3706   0.7557
   9.500   1.6698   0.04193   0.03429  -0.1340   0.3617   0.7606
   9.750   1.6857   0.04218   0.03449  -0.1324   0.3533   0.7666
  10.000   1.6834   0.04349   0.03586  -0.1292   0.3444   0.7713
  10.250   1.7075   0.04346   0.03571  -0.1286   0.3369   0.7787
  10.500   1.6901   0.04604   0.03848  -0.1246   0.3288   0.7834
  10.750   1.7405   0.04446   0.03661  -0.1262   0.3220   0.7952
  11.000   1.6995   0.04898   0.04149  -0.1212   0.3150   0.7979
  11.250   1.7195   0.04935   0.04180  -0.1204   0.3085   0.8080
  11.500   1.7336   0.05030   0.04276  -0.1194   0.3028   0.8189
  11.750   1.7055   0.05477   0.04750  -0.1167   0.2969   0.8252
  12.000   1.7281   0.05451   0.04725  -0.1156   0.2917   0.8870
  12.250   1.7457   0.05550   0.04818  -0.1151   0.2868   1.0000
  12.500   1.6956   0.06280   0.05583  -0.1129   0.2821   1.0000
  12.750   1.6997   0.06517   0.05823  -0.1123   0.2773   1.0000
  13.000   1.7879   0.05967   0.05223  -0.1133   0.2722   1.0000
  13.250   1.7095   0.07001   0.06310  -0.1113   0.2689   1.0000
  13.500   1.0221   0.20349   0.19778  -0.1680   0.3000   0.7565
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