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GOE 431 AIRFOIL (goe431-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 431 AIRFOIL (goe431-il)
Reynolds number: 50,000
Max Cl/Cd: 39.51 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe431-il-50000-n5.txt
Download as CSV file: xf-goe431-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 431 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.2554   0.10809   0.10174  -0.0545   0.9540   0.0578
  -7.500  -0.2564   0.10513   0.09881  -0.0556   0.9512   0.0580
  -7.250  -0.2649   0.10276   0.09650  -0.0546   0.9473   0.0581
  -7.000  -0.2731   0.10026   0.09405  -0.0539   0.9431   0.0581
  -6.750  -0.2761   0.09694   0.09077  -0.0550   0.9398   0.0582
  -6.500  -0.2756   0.09305   0.08691  -0.0574   0.9371   0.0583
  -6.250  -0.2777   0.08905   0.08296  -0.0595   0.9340   0.0588
  -6.000  -0.2799   0.08455   0.07849  -0.0622   0.9300   0.0596
  -5.750  -0.2742   0.07705   0.07098  -0.0702   0.9265   0.0610
  -5.500  -0.2567   0.07080   0.06470  -0.0783   0.9243   0.0638
  -5.250  -0.1653   0.04757   0.04046  -0.1213   0.9245   0.0752
  -5.000  -0.1649   0.05293   0.04630  -0.1105   0.9219   0.0788
  -4.500  -0.0858   0.04848   0.04130  -0.1231   0.9183   0.1101
  -4.000  -0.0222   0.04707   0.03929  -0.1290   0.9142   0.1519
  -3.500   0.0330   0.04697   0.03877  -0.1308   0.9091   0.1866
  -3.250   0.0642   0.04672   0.03825  -0.1325   0.9071   0.2021
  -3.000   0.0939   0.04676   0.03808  -0.1337   0.9047   0.2170
  -2.750   0.1165   0.04654   0.03766  -0.1341   0.9003   0.2304
  -2.500   0.1510   0.04623   0.03717  -0.1356   0.8931   0.2396
  -2.250   0.1978   0.04470   0.03512  -0.1405   0.8829   0.2454
  -2.000   0.2428   0.04388   0.03408  -0.1436   0.8726   0.2499
  -1.750   0.2887   0.04268   0.03254  -0.1472   0.8618   0.2530
  -1.500   0.3245   0.04177   0.03132  -0.1491   0.8512   0.2552
  -1.250   0.3737   0.04080   0.02992  -0.1532   0.8452   0.2590
  -1.000   0.3959   0.04058   0.02963  -0.1526   0.8361   0.2617
  -0.750   0.4368   0.04004   0.02894  -0.1548   0.8304   0.2653
  -0.500   0.4606   0.03983   0.02862  -0.1545   0.8212   0.2678
  -0.250   0.5023   0.03923   0.02781  -0.1568   0.8152   0.2710
   0.000   0.5277   0.03906   0.02747  -0.1566   0.8054   0.2740
   0.250   0.5687   0.03849   0.02679  -0.1585   0.7993   0.2776
   0.500   0.5913   0.03842   0.02668  -0.1576   0.7882   0.2813
   0.750   0.6351   0.03773   0.02584  -0.1596   0.7824   0.2891
   1.000   0.6561   0.03766   0.02578  -0.1584   0.7698   0.2946
   1.250   0.6813   0.03745   0.02556  -0.1577   0.7580   0.3013
   1.500   0.7225   0.03662   0.02470  -0.1591   0.7511   0.3103
   1.750   0.7448   0.03641   0.02452  -0.1579   0.7370   0.3186
   2.000   0.7683   0.03612   0.02430  -0.1568   0.7224   0.3285
   2.250   0.7922   0.03581   0.02406  -0.1557   0.7072   0.3419
   2.500   0.8160   0.03547   0.02386  -0.1546   0.6911   0.3605
   3.000   0.8526   0.03538   0.02412  -0.1512   0.6483   0.4121
   3.250   0.8779   0.03495   0.02389  -0.1502   0.6296   0.4552
   3.500   0.9015   0.03473   0.02383  -0.1491   0.6081   0.5078
   3.750   0.9336   0.03391   0.02313  -0.1487   0.5925   0.5799
   4.000   0.9657   0.03250   0.02216  -0.1479   0.5793   0.7037
   4.250   0.9988   0.03154   0.02104  -0.1475   0.5660   1.0000
   4.750   1.0746   0.03070   0.01972  -0.1487   0.5410   1.0000
   5.000   1.1078   0.03076   0.01959  -0.1491   0.5289   1.0000
   5.250   1.1416   0.03091   0.01957  -0.1496   0.5185   1.0000
   5.500   1.1739   0.03122   0.01976  -0.1500   0.5088   1.0000
   5.750   1.2036   0.03172   0.02021  -0.1503   0.5003   1.0000
   6.000   1.2366   0.03217   0.02063  -0.1510   0.4930   1.0000
   6.250   1.2678   0.03274   0.02121  -0.1516   0.4865   1.0000
   6.500   1.2963   0.03342   0.02194  -0.1519   0.4797   1.0000
   7.000   1.3572   0.03479   0.02349  -0.1531   0.4677   1.0000
   7.250   1.3876   0.03553   0.02434  -0.1537   0.4623   1.0000
   7.500   1.4280   0.03614   0.02505  -0.1558   0.4580   1.0000
   7.750   1.4446   0.03727   0.02640  -0.1545   0.4527   1.0000
   8.000   1.4680   0.03820   0.02748  -0.1541   0.4464   1.0000
   8.250   1.4972   0.03899   0.02836  -0.1544   0.4395   1.0000
   8.500   1.5077   0.04018   0.02980  -0.1521   0.4321   1.0000
   8.750   1.5372   0.04086   0.03054  -0.1523   0.4240   1.0000
   9.000   1.5407   0.04217   0.03210  -0.1490   0.4161   1.0000
   9.250   1.5724   0.04280   0.03281  -0.1495   0.4086   1.0000
   9.500   1.5705   0.04443   0.03474  -0.1457   0.4023   1.0000
   9.750   1.5937   0.04534   0.03587  -0.1451   0.3958   1.0000
  10.000   1.6023   0.04675   0.03752  -0.1428   0.3895   1.0000
  10.250   1.6063   0.04832   0.03935  -0.1399   0.3829   1.0000
  10.500   1.6342   0.04902   0.04023  -0.1398   0.3761   1.0000
  10.750   1.6179   0.05149   0.04302  -0.1349   0.3696   1.0000
  11.000   1.6521   0.05156   0.04323  -0.1351   0.3608   1.0000
  11.250   1.6224   0.05490   0.04691  -0.1293   0.3544   1.0000
  11.500   1.6314   0.05542   0.04753  -0.1267   0.3422   1.0000
  12.000   1.5981   0.06050   0.05305  -0.1188   0.3209   1.0000
  12.250   1.5863   0.06253   0.05518  -0.1155   0.3076   1.0000
  12.500   1.5727   0.06497   0.05773  -0.1125   0.2942   1.0000
  12.750   1.5431   0.07042   0.06346  -0.1103   0.2858   1.0000
  13.000   1.5189   0.07547   0.06871  -0.1089   0.2756   1.0000
  13.250   1.4981   0.08039   0.07377  -0.1080   0.2638   1.0000
  13.500   1.4547   0.09056   0.08420  -0.1093   0.2587   1.0000
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