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GOE 430 AIRFOIL (goe430-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 430 AIRFOIL (goe430-il)
Reynolds number: 500,000
Max Cl/Cd: 111.41 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe430-il-500000.txt
Download as CSV file: xf-goe430-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 430 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
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.3692   0.12602   0.12347  -0.0498   1.0000   0.0449
 -12.750  -0.7577   0.05414   0.05128  -0.0849   1.0000   0.0434
 -12.500  -0.7846   0.04214   0.03891  -0.1034   0.9921   0.0437
 -12.250  -0.7566   0.03541   0.03177  -0.1214   0.9851   0.0445
 -12.000  -0.7295   0.03112   0.02715  -0.1303   0.9825   0.0457
 -11.750  -0.7030   0.02983   0.02587  -0.1323   0.9789   0.0466
 -11.500  -0.6718   0.02882   0.02482  -0.1350   0.9758   0.0476
 -11.250  -0.6372   0.02772   0.02363  -0.1384   0.9736   0.0488
 -11.000  -0.6023   0.02648   0.02224  -0.1419   0.9715   0.0500
 -10.750  -0.5674   0.02533   0.02091  -0.1451   0.9695   0.0512
 -10.500  -0.5400   0.02468   0.02009  -0.1463   0.9645   0.0520
 -10.250  -0.5141   0.02238   0.01756  -0.1485   0.9605   0.0531
 -10.000  -0.4849   0.02098   0.01611  -0.1500   0.9576   0.0541
  -9.750  -0.4543   0.02014   0.01522  -0.1514   0.9552   0.0551
  -9.500  -0.4287   0.01943   0.01443  -0.1517   0.9503   0.0559
  -9.250  -0.4010   0.01864   0.01355  -0.1523   0.9461   0.0567
  -9.000  -0.3722   0.01788   0.01269  -0.1530   0.9426   0.0575
  -8.750  -0.3433   0.01722   0.01193  -0.1536   0.9392   0.0584
  -8.500  -0.3171   0.01669   0.01130  -0.1536   0.9337   0.0593
  -8.250  -0.2893   0.01613   0.01065  -0.1538   0.9289   0.0599
  -8.000  -0.2609   0.01564   0.01005  -0.1540   0.9245   0.0604
  -7.750  -0.2345   0.01475   0.00907  -0.1541   0.9191   0.0613
  -7.500  -0.2073   0.01396   0.00824  -0.1543   0.9137   0.0625
  -7.250  -0.1791   0.01343   0.00767  -0.1546   0.9094   0.0637
  -7.000  -0.1508   0.01304   0.00723  -0.1548   0.9048   0.0649
  -6.750  -0.1228   0.01266   0.00682  -0.1549   0.8990   0.0663
  -6.500  -0.0943   0.01230   0.00639  -0.1550   0.8938   0.0676
  -6.250  -0.0655   0.01198   0.00600  -0.1551   0.8890   0.0688
  -6.000  -0.0371   0.01170   0.00566  -0.1552   0.8831   0.0698
  -5.750  -0.0082   0.01123   0.00516  -0.1555   0.8775   0.0720
  -5.500   0.0209   0.01090   0.00479  -0.1557   0.8723   0.0745
  -5.250   0.0497   0.01063   0.00451  -0.1558   0.8658   0.0773
  -5.000   0.0788   0.01041   0.00424  -0.1559   0.8603   0.0805
  -4.750   0.1082   0.01010   0.00395  -0.1562   0.8549   0.0875
  -4.500   0.1373   0.00983   0.00375  -0.1564   0.8481   0.0999
  -4.250   0.1665   0.00965   0.00362  -0.1566   0.8421   0.1209
  -4.000   0.1955   0.00957   0.00354  -0.1566   0.8356   0.1346
  -3.750   0.2244   0.00949   0.00345  -0.1567   0.8285   0.1441
  -3.500   0.2536   0.00939   0.00330  -0.1568   0.8221   0.1513
  -3.250   0.2825   0.00927   0.00320  -0.1569   0.8138   0.1583
  -3.000   0.3115   0.00923   0.00307  -0.1569   0.8066   0.1632
  -2.750   0.3405   0.00905   0.00292  -0.1570   0.7972   0.1698
  -2.500   0.3696   0.00896   0.00279  -0.1571   0.7888   0.1761
  -2.250   0.3984   0.00886   0.00268  -0.1572   0.7783   0.1828
  -2.000   0.4273   0.00875   0.00257  -0.1572   0.7669   0.1912
  -1.750   0.4559   0.00867   0.00247  -0.1572   0.7541   0.2016
  -1.500   0.4844   0.00859   0.00240  -0.1572   0.7405   0.2184
  -1.250   0.5130   0.00853   0.00238  -0.1573   0.7265   0.2479
  -1.000   0.5415   0.00850   0.00237  -0.1573   0.7130   0.2784
  -0.750   0.5699   0.00849   0.00237  -0.1573   0.6994   0.3025
  -0.500   0.5980   0.00850   0.00237  -0.1572   0.6852   0.3246
  -0.250   0.6260   0.00853   0.00239  -0.1571   0.6710   0.3452
   0.000   0.6539   0.00858   0.00242  -0.1570   0.6575   0.3644
   0.250   0.6818   0.00863   0.00247  -0.1569   0.6442   0.3857
   0.500   0.7099   0.00867   0.00255  -0.1569   0.6319   0.4128
   0.750   0.7378   0.00874   0.00264  -0.1568   0.6201   0.4414
   1.000   0.7653   0.00884   0.00273  -0.1566   0.6076   0.4679
   1.250   0.7927   0.00895   0.00283  -0.1564   0.5937   0.4914
   1.500   0.8200   0.00904   0.00293  -0.1562   0.5786   0.5140
   1.750   0.8472   0.00915   0.00304  -0.1560   0.5638   0.5361
   2.000   0.8745   0.00925   0.00316  -0.1557   0.5503   0.5577
   2.250   0.9014   0.00938   0.00329  -0.1555   0.5369   0.5805
   2.500   0.9282   0.00952   0.00343  -0.1552   0.5237   0.6028
   2.750   0.9548   0.00968   0.00358  -0.1548   0.5106   0.6240
   3.000   0.9817   0.00983   0.00373  -0.1545   0.4990   0.6437
   3.250   1.0083   0.00999   0.00388  -0.1542   0.4883   0.6629
   3.750   1.0611   0.01029   0.00421  -0.1535   0.4680   0.7015
   4.000   1.0870   0.01046   0.00438  -0.1531   0.4595   0.7220
   4.250   1.1134   0.01054   0.00456  -0.1527   0.4512   0.7468
   4.500   1.1382   0.01064   0.00475  -0.1520   0.4434   0.7877
   4.750   1.1582   0.01043   0.00484  -0.1501   0.4359   1.0000
   5.000   1.1841   0.01069   0.00504  -0.1497   0.4276   1.0000
   5.250   1.2110   0.01087   0.00522  -0.1495   0.4194   1.0000
   5.500   1.2363   0.01115   0.00544  -0.1490   0.4102   1.0000
   5.750   1.2625   0.01134   0.00565  -0.1487   0.3998   1.0000
   6.000   1.2875   0.01160   0.00587  -0.1482   0.3860   1.0000
   6.250   1.3120   0.01189   0.00611  -0.1476   0.3693   1.0000
   6.500   1.3348   0.01226   0.00638  -0.1467   0.3436   1.0000
   6.750   1.3488   0.01323   0.00693  -0.1445   0.2714   1.0000
   7.000   1.3637   0.01418   0.00762  -0.1424   0.2387   1.0000
   7.250   1.3827   0.01478   0.00815  -0.1410   0.2251   1.0000
   7.500   1.4031   0.01527   0.00861  -0.1398   0.2160   1.0000
   7.750   1.4218   0.01583   0.00913  -0.1383   0.2072   1.0000
   8.000   1.4419   0.01623   0.00954  -0.1370   0.1999   1.0000
   8.250   1.4589   0.01674   0.01003  -0.1351   0.1926   1.0000
   8.500   1.4776   0.01717   0.01049  -0.1336   0.1854   1.0000
   8.750   1.4950   0.01770   0.01099  -0.1320   0.1764   1.0000
   9.000   1.5133   0.01817   0.01147  -0.1305   0.1676   1.0000
   9.250   1.5294   0.01878   0.01204  -0.1287   0.1564   1.0000
   9.500   1.5444   0.01946   0.01267  -0.1269   0.1416   1.0000
   9.750   1.5570   0.02030   0.01342  -0.1248   0.1254   1.0000
  10.000   1.5681   0.02125   0.01430  -0.1225   0.1118   1.0000
  10.250   1.5784   0.02227   0.01527  -0.1203   0.1023   1.0000
  10.500   1.5883   0.02336   0.01633  -0.1181   0.0951   1.0000
  10.750   1.5991   0.02441   0.01739  -0.1161   0.0892   1.0000
  11.000   1.6074   0.02567   0.01864  -0.1140   0.0834   1.0000
  11.250   1.6188   0.02674   0.01975  -0.1122   0.0778   1.0000
  11.500   1.6256   0.02818   0.02117  -0.1101   0.0694   1.0000
  11.750   1.6273   0.03005   0.02289  -0.1076   0.0436   1.0000
  12.000   1.6188   0.03285   0.02556  -0.1045   0.0294   1.0000
  12.250   1.6204   0.03493   0.02769  -0.1023   0.0261   1.0000
  12.500   1.6217   0.03710   0.02991  -0.1004   0.0242   1.0000
  12.750   1.6249   0.03916   0.03206  -0.0987   0.0229   1.0000
  13.000   1.6283   0.04126   0.03425  -0.0972   0.0219   1.0000
  13.250   1.6293   0.04367   0.03673  -0.0957   0.0210   1.0000
  13.500   1.6277   0.04643   0.03958  -0.0943   0.0203   1.0000
  13.750   1.6232   0.04964   0.04288  -0.0931   0.0197   1.0000
  14.000   1.6251   0.05227   0.04561  -0.0922   0.0193   1.0000
  14.250   1.6252   0.05515   0.04860  -0.0915   0.0189   1.0000
  14.500   1.6238   0.05830   0.05184  -0.0908   0.0185   1.0000
  14.750   1.6211   0.06167   0.05532  -0.0904   0.0181   1.0000
  15.000   1.6175   0.06525   0.05900  -0.0900   0.0177   1.0000
  15.250   1.6125   0.06908   0.06292  -0.0899   0.0174   1.0000
  15.500   1.6054   0.07324   0.06718  -0.0898   0.0171   1.0000
  15.750   1.5959   0.07783   0.07187  -0.0900   0.0169   1.0000
  16.000   1.5839   0.08286   0.07700  -0.0904   0.0166   1.0000
  16.250   1.5718   0.08795   0.08219  -0.0910   0.0164   1.0000
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