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GOE 164 (MVA MK.10) AIRFOIL (goe164-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 164 (MVA MK.10) AIRFOIL (goe164-il)
Reynolds number: 1,000,000
Max Cl/Cd: 102.11 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe164-il-1000000-n5.txt
Download as CSV file: xf-goe164-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 164 (MVA MK.10) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.1820   0.10301   0.10129  -0.0593   0.9873   0.0049
  -9.500  -0.1693   0.09970   0.09798  -0.0620   0.9858   0.0050
  -8.500  -0.2096   0.03102   0.02873  -0.1386   0.9585   0.0050
  -8.000  -0.1413   0.01653   0.01335  -0.1574   0.9460   0.0052
  -7.750  -0.1076   0.01497   0.01156  -0.1598   0.9396   0.0053
  -7.250  -0.0422   0.01279   0.00898  -0.1630   0.9050   0.0057
  -7.000  -0.0099   0.01216   0.00791  -0.1642   0.8388   0.0060
  -6.750   0.0148   0.01180   0.00725  -0.1636   0.8045   0.0062
  -6.500   0.0406   0.01147   0.00671  -0.1632   0.7827   0.0065
  -6.250   0.0671   0.01096   0.00600  -0.1631   0.7663   0.0068
  -6.000   0.0941   0.01047   0.00535  -0.1630   0.7530   0.0072
  -5.750   0.1213   0.01016   0.00492  -0.1628   0.7409   0.0076
  -5.500   0.1482   0.00990   0.00453  -0.1626   0.7260   0.0081
  -5.250   0.1749   0.00969   0.00417  -0.1622   0.7076   0.0086
  -5.000   0.2016   0.00951   0.00383  -0.1619   0.6879   0.0090
  -4.750   0.2286   0.00934   0.00352  -0.1616   0.6705   0.0095
  -4.500   0.2558   0.00910   0.00316  -0.1614   0.6526   0.0107
  -4.250   0.2830   0.00898   0.00294  -0.1611   0.6355   0.0120
  -4.000   0.3102   0.00889   0.00273  -0.1609   0.6177   0.0131
  -3.750   0.3373   0.00878   0.00249  -0.1606   0.5977   0.0153
  -3.500   0.3641   0.00874   0.00234  -0.1602   0.5750   0.0179
  -3.250   0.3911   0.00870   0.00222  -0.1600   0.5552   0.0225
  -3.000   0.4184   0.00870   0.00212  -0.1597   0.5391   0.0262
  -2.750   0.4455   0.00868   0.00202  -0.1595   0.5210   0.0305
  -2.500   0.4722   0.00873   0.00195  -0.1591   0.4964   0.0345
  -2.250   0.4987   0.00882   0.00189  -0.1588   0.4691   0.0381
  -2.000   0.5254   0.00887   0.00183  -0.1584   0.4422   0.0446
  -1.750   0.5516   0.00900   0.00180  -0.1581   0.4077   0.0534
  -1.500   0.5775   0.00898   0.00178  -0.1578   0.3714   0.1075
  -1.250   0.6038   0.00913   0.00184  -0.1574   0.3471   0.1270
  -1.000   0.6306   0.00926   0.00189  -0.1571   0.3305   0.1364
  -0.750   0.6575   0.00938   0.00193  -0.1568   0.3176   0.1426
  -0.500   0.6846   0.00948   0.00197  -0.1566   0.3088   0.1465
  -0.250   0.7119   0.00954   0.00201  -0.1564   0.3029   0.1514
   0.000   0.7392   0.00962   0.00205  -0.1562   0.2965   0.1564
   0.250   0.7663   0.00971   0.00212  -0.1559   0.2904   0.1626
   0.500   0.7936   0.00978   0.00218  -0.1557   0.2848   0.1684
   0.750   0.8205   0.00989   0.00224  -0.1555   0.2768   0.1710
   1.000   0.8474   0.01000   0.00230  -0.1552   0.2680   0.1732
   1.250   0.8740   0.01013   0.00237  -0.1549   0.2568   0.1758
   1.500   0.9002   0.01030   0.00247  -0.1546   0.2409   0.1798
   1.750   0.9223   0.01090   0.00277  -0.1536   0.1793   0.1830
   2.000   0.9481   0.01112   0.00292  -0.1531   0.1684   0.1860
   2.250   0.9744   0.01127   0.00305  -0.1528   0.1631   0.1885
   2.500   1.0008   0.01139   0.00318  -0.1525   0.1598   0.1920
   2.750   1.0269   0.01155   0.00333  -0.1521   0.1556   0.1960
   3.000   1.0530   0.01170   0.00347  -0.1518   0.1525   0.2001
   3.500   1.1056   0.01194   0.00375  -0.1511   0.1487   0.2103
   3.750   1.1319   0.01206   0.00389  -0.1508   0.1472   0.2159
   4.000   1.1579   0.01219   0.00405  -0.1505   0.1452   0.2225
   4.250   1.1838   0.01234   0.00422  -0.1501   0.1426   0.2316
   4.500   1.2093   0.01250   0.00441  -0.1497   0.1394   0.2459
   4.750   1.2347   0.01266   0.00463  -0.1493   0.1358   0.2813
   5.000   1.2606   0.01275   0.00486  -0.1491   0.1338   0.3477
   5.250   1.2860   0.01290   0.00507  -0.1487   0.1300   0.3849
   5.500   1.3104   0.01312   0.00533  -0.1482   0.1203   0.4328
   6.000   1.3509   0.01323   0.00620  -0.1456   0.0828   1.0000
   6.250   1.3745   0.01354   0.00651  -0.1449   0.0783   1.0000
   6.500   1.3981   0.01385   0.00683  -0.1442   0.0759   1.0000
   6.750   1.4211   0.01419   0.00718  -0.1433   0.0733   1.0000
   7.000   1.4439   0.01454   0.00755  -0.1425   0.0702   1.0000
   7.250   1.4674   0.01480   0.00783  -0.1418   0.0687   1.0000
   7.500   1.4908   0.01505   0.00812  -0.1411   0.0663   1.0000
   7.750   1.5116   0.01552   0.00853  -0.1399   0.0560   1.0000
   8.000   1.5229   0.01673   0.00951  -0.1372   0.0153   1.0000
   8.250   1.5422   0.01724   0.01003  -0.1358   0.0113   1.0000
   8.500   1.5615   0.01773   0.01054  -0.1344   0.0096   1.0000
   8.750   1.5792   0.01826   0.01110  -0.1327   0.0079   1.0000
   9.000   1.5963   0.01874   0.01161  -0.1309   0.0071   1.0000
   9.250   1.6120   0.01928   0.01219  -0.1289   0.0064   1.0000
   9.500   1.6263   0.01991   0.01285  -0.1267   0.0056   1.0000
   9.750   1.6413   0.02048   0.01348  -0.1247   0.0053   1.0000
  10.000   1.6554   0.02110   0.01415  -0.1225   0.0049   1.0000
  10.250   1.6687   0.02177   0.01487  -0.1203   0.0045   1.0000
  10.500   1.6805   0.02253   0.01568  -0.1179   0.0042   1.0000
  10.750   1.6905   0.02343   0.01663  -0.1154   0.0038   1.0000
  11.000   1.7019   0.02424   0.01751  -0.1131   0.0037   1.0000
  11.250   1.7119   0.02517   0.01851  -0.1108   0.0035   1.0000
  11.500   1.7212   0.02617   0.01958  -0.1084   0.0033   1.0000
  11.750   1.7296   0.02727   0.02077  -0.1061   0.0032   1.0000
  12.000   1.7371   0.02848   0.02204  -0.1039   0.0030   1.0000
  12.250   1.7432   0.02984   0.02348  -0.1016   0.0029   1.0000
  12.500   1.7477   0.03142   0.02514  -0.0995   0.0027   1.0000
  12.750   1.7500   0.03328   0.02709  -0.0973   0.0026   1.0000
  13.000   1.7491   0.03557   0.02949  -0.0953   0.0025   1.0000
  13.250   1.7513   0.03771   0.03172  -0.0938   0.0025   1.0000
  13.500   1.7526   0.04005   0.03417  -0.0925   0.0024   1.0000
  13.750   1.7521   0.04268   0.03690  -0.0914   0.0024   1.0000
  14.000   1.7508   0.04551   0.03984  -0.0904   0.0023   1.0000
  14.250   1.7477   0.04867   0.04311  -0.0897   0.0023   1.0000
  14.500   1.7432   0.05210   0.04666  -0.0892   0.0022   1.0000
  14.750   1.7377   0.05578   0.05046  -0.0888   0.0021   1.0000
  15.000   1.7311   0.05974   0.05453  -0.0888   0.0021   1.0000
  15.250   1.7233   0.06398   0.05889  -0.0889   0.0020   1.0000
  15.500   1.7142   0.06851   0.06354  -0.0893   0.0020   1.0000
  15.750   1.7032   0.07347   0.06861  -0.0899   0.0020   1.0000
  16.000   1.6906   0.07880   0.07407  -0.0908   0.0019   1.0000
  16.250   1.6783   0.08414   0.07953  -0.0918   0.0019   1.0000
  16.500   1.6643   0.08985   0.08536  -0.0930   0.0019   1.0000
  16.750   1.6489   0.09591   0.09154  -0.0945   0.0019   1.0000
  17.000   1.6360   0.10165   0.09739  -0.0960   0.0018   1.0000
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