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GOE 358 AIRFOIL (goe358-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 358 AIRFOIL (goe358-il)
Reynolds number: 500,000
Max Cl/Cd: 105.71 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe358-il-500000.txt
Download as CSV file: xf-goe358-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 358 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  -0.3573   0.12560   0.12308  -0.0304   1.0000   0.0313
 -11.250  -0.7328   0.05280   0.05011  -0.0644   1.0000   0.0250
 -11.000  -0.7604   0.04305   0.04013  -0.0756   1.0000   0.0250
 -10.750  -0.7481   0.03447   0.03127  -0.0900   1.0000   0.0256
 -10.500  -0.7232   0.03213   0.02889  -0.0943   1.0000   0.0262
 -10.250  -0.6953   0.02975   0.02640  -0.0990   1.0000   0.0270
 -10.000  -0.6650   0.02698   0.02339  -0.1044   0.9999   0.0280
  -9.750  -0.6254   0.02463   0.02065  -0.1103   0.9986   0.0294
  -9.500  -0.5896   0.02326   0.01921  -0.1138   0.9971   0.0307
  -9.250  -0.5535   0.02313   0.01910  -0.1160   0.9955   0.0317
  -9.000  -0.5158   0.02225   0.01805  -0.1191   0.9942   0.0333
  -8.750  -0.4795   0.02122   0.01673  -0.1220   0.9923   0.0348
  -8.500  -0.4455   0.02020   0.01569  -0.1242   0.9902   0.0363
  -8.250  -0.4099   0.02012   0.01561  -0.1261   0.9880   0.0376
  -8.000  -0.3729   0.01963   0.01498  -0.1284   0.9862   0.0396
  -7.750  -0.3344   0.01926   0.01439  -0.1309   0.9846   0.0411
  -7.500  -0.2978   0.01792   0.01305  -0.1336   0.9835   0.0432
  -7.250  -0.2634   0.01764   0.01273  -0.1351   0.9805   0.0450
  -7.000  -0.2276   0.01715   0.01214  -0.1369   0.9771   0.0470
  -6.750  -0.1888   0.01698   0.01181  -0.1390   0.9746   0.0485
  -6.500  -0.1512   0.01535   0.01015  -0.1419   0.9731   0.0512
  -6.250  -0.1116   0.01483   0.00959  -0.1444   0.9717   0.0532
  -6.000  -0.0700   0.01431   0.00900  -0.1472   0.9705   0.0555
  -5.750  -0.0379   0.01393   0.00854  -0.1479   0.9644   0.0571
  -5.500  -0.0010   0.01294   0.00745  -0.1499   0.9606   0.0589
  -5.250   0.0360   0.01211   0.00662  -0.1518   0.9570   0.0612
  -5.000   0.0651   0.01163   0.00612  -0.1518   0.9484   0.0628
  -4.750   0.0974   0.01120   0.00565  -0.1524   0.9423   0.0648
  -4.500   0.1257   0.01085   0.00525  -0.1523   0.9335   0.0664
  -4.250   0.1563   0.01049   0.00483  -0.1525   0.9262   0.0676
  -4.000   0.1841   0.01025   0.00454  -0.1522   0.9150   0.0685
  -3.750   0.2134   0.00968   0.00392  -0.1523   0.9038   0.0713
  -3.500   0.2423   0.00936   0.00355  -0.1523   0.8915   0.0735
  -3.250   0.2710   0.00912   0.00325  -0.1522   0.8778   0.0758
  -3.000   0.2995   0.00894   0.00299  -0.1520   0.8623   0.0782
  -2.750   0.3279   0.00881   0.00277  -0.1517   0.8452   0.0807
  -2.500   0.3565   0.00861   0.00250  -0.1516   0.8271   0.0869
  -2.250   0.3849   0.00846   0.00230  -0.1515   0.8086   0.0979
  -2.000   0.4136   0.00805   0.00208  -0.1517   0.7905   0.1755
  -1.750   0.4417   0.00788   0.00208  -0.1516   0.7731   0.2648
  -1.500   0.4695   0.00797   0.00212  -0.1513   0.7569   0.2913
  -1.250   0.4973   0.00808   0.00216  -0.1510   0.7419   0.3075
  -1.000   0.5252   0.00819   0.00223  -0.1507   0.7279   0.3192
  -0.750   0.5530   0.00831   0.00227  -0.1504   0.7142   0.3286
  -0.500   0.5808   0.00843   0.00232  -0.1502   0.7004   0.3361
  -0.250   0.6087   0.00853   0.00235  -0.1499   0.6860   0.3427
   0.000   0.6365   0.00862   0.00242  -0.1496   0.6709   0.3502
   0.250   0.6641   0.00876   0.00247  -0.1493   0.6537   0.3575
   0.500   0.6913   0.00886   0.00253  -0.1490   0.6341   0.3642
   0.750   0.7185   0.00899   0.00258  -0.1486   0.6108   0.3700
   1.000   0.7452   0.00917   0.00264  -0.1481   0.5856   0.3762
   1.250   0.7719   0.00934   0.00274  -0.1477   0.5602   0.3823
   1.500   0.7983   0.00958   0.00284  -0.1473   0.5365   0.3887
   1.750   0.8250   0.00975   0.00295  -0.1469   0.5141   0.3944
   2.000   0.8516   0.00995   0.00308  -0.1465   0.4932   0.3994
   2.250   0.8781   0.01017   0.00319  -0.1461   0.4738   0.4038
   2.500   0.9047   0.01037   0.00331  -0.1457   0.4561   0.4079
   2.750   0.9314   0.01053   0.00344  -0.1454   0.4407   0.4121
   3.000   0.9583   0.01070   0.00359  -0.1451   0.4278   0.4168
   3.250   0.9851   0.01089   0.00373  -0.1448   0.4155   0.4221
   3.500   1.0116   0.01107   0.00389  -0.1444   0.4043   0.4272
   3.750   1.0384   0.01123   0.00406  -0.1441   0.3952   0.4325
   4.000   1.0651   0.01142   0.00423  -0.1438   0.3873   0.4381
   4.250   1.0917   0.01157   0.00441  -0.1434   0.3790   0.4436
   4.500   1.1182   0.01175   0.00460  -0.1431   0.3725   0.4499
   4.750   1.1451   0.01189   0.00478  -0.1428   0.3665   0.4565
   5.000   1.1711   0.01210   0.00501  -0.1423   0.3601   0.4638
   5.250   1.1979   0.01224   0.00520  -0.1420   0.3533   0.4718
   5.500   1.2238   0.01242   0.00541  -0.1416   0.3453   0.4799
   5.750   1.2502   0.01258   0.00563  -0.1413   0.3380   0.4891
   6.000   1.2757   0.01278   0.00585  -0.1408   0.3286   0.4995
   6.250   1.3019   0.01291   0.00607  -0.1404   0.3188   0.5120
   6.500   1.3273   0.01311   0.00631  -0.1399   0.3081   0.5285
   6.750   1.3523   0.01331   0.00658  -0.1394   0.2953   0.5541
   7.000   1.3755   0.01305   0.00688  -0.1386   0.2792   0.8106
   7.250   1.3975   0.01322   0.00708  -0.1373   0.2524   1.0000
   7.500   1.4132   0.01441   0.00777  -0.1355   0.1766   1.0000
   7.750   1.4316   0.01533   0.00852  -0.1340   0.1504   1.0000
   8.000   1.4515   0.01606   0.00915  -0.1327   0.1254   1.0000
   8.250   1.4673   0.01715   0.00994  -0.1309   0.0853   1.0000
   8.500   1.4846   0.01805   0.01073  -0.1292   0.0706   1.0000
   8.750   1.5033   0.01875   0.01142  -0.1277   0.0636   1.0000
   9.000   1.5211   0.01949   0.01217  -0.1261   0.0575   1.0000
   9.250   1.5376   0.02027   0.01295  -0.1243   0.0522   1.0000
   9.500   1.5540   0.02100   0.01372  -0.1224   0.0478   1.0000
   9.750   1.5690   0.02176   0.01449  -0.1203   0.0438   1.0000
  10.000   1.5801   0.02260   0.01537  -0.1176   0.0405   1.0000
  10.250   1.5934   0.02329   0.01610  -0.1153   0.0377   1.0000
  10.500   1.6005   0.02439   0.01721  -0.1122   0.0351   1.0000
  10.750   1.6119   0.02525   0.01815  -0.1098   0.0333   1.0000
  11.000   1.6224   0.02619   0.01915  -0.1074   0.0316   1.0000
  11.250   1.6295   0.02740   0.02039  -0.1048   0.0301   1.0000
  11.500   1.6302   0.02913   0.02218  -0.1016   0.0287   1.0000
  11.750   1.6393   0.03032   0.02347  -0.0996   0.0276   1.0000
  12.000   1.6463   0.03172   0.02496  -0.0975   0.0265   1.0000
  12.250   1.6519   0.03331   0.02662  -0.0955   0.0256   1.0000
  12.500   1.6529   0.03539   0.02876  -0.0934   0.0247   1.0000
  12.750   1.6457   0.03839   0.03185  -0.0912   0.0239   1.0000
  13.000   1.6489   0.04055   0.03412  -0.0898   0.0234   1.0000
  13.250   1.6512   0.04291   0.03660  -0.0886   0.0228   1.0000
  13.500   1.6521   0.04552   0.03932  -0.0876   0.0223   1.0000
  13.750   1.6517   0.04836   0.04226  -0.0868   0.0217   1.0000
  14.000   1.6504   0.05140   0.04538  -0.0862   0.0212   1.0000
  14.250   1.6477   0.05469   0.04877  -0.0858   0.0208   1.0000
  14.500   1.6425   0.05835   0.05251  -0.0855   0.0204   1.0000
  14.750   1.6335   0.06255   0.05680  -0.0853   0.0200   1.0000
  15.000   1.6222   0.06708   0.06143  -0.0851   0.0196   1.0000
  15.250   1.6209   0.07058   0.06505  -0.0853   0.0193   1.0000
  15.500   1.6181   0.07432   0.06891  -0.0856   0.0190   1.0000
  15.750   1.6147   0.07821   0.07292  -0.0860   0.0186   1.0000
  16.000   1.6106   0.08224   0.07707  -0.0866   0.0183   1.0000
  16.250   1.6060   0.08636   0.08129  -0.0872   0.0179   1.0000
  16.500   1.6014   0.09054   0.08556  -0.0879   0.0176   1.0000
  16.750   1.5969   0.09474   0.08986  -0.0888   0.0174   1.0000
  17.000   1.5924   0.09898   0.09418  -0.0897   0.0171   1.0000
  17.250   1.5878   0.10322   0.09849  -0.0907   0.0168   1.0000
  17.500   1.5831   0.10742   0.10276  -0.0917   0.0166   1.0000
  17.750   1.5782   0.11150   0.10691  -0.0925   0.0163   1.0000
  18.000   1.5723   0.11539   0.11087  -0.0928   0.0160   1.0000
  18.250   1.5676   0.12003   0.11565  -0.0945   0.0158   1.0000
  18.500   1.5628   0.12467   0.12043  -0.0964   0.0157   1.0000
  18.750   1.5574   0.12942   0.12532  -0.0983   0.0155   1.0000
  19.000   1.5521   0.13423   0.13025  -0.1004   0.0153   1.0000
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