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GOE 476 AIRFOIL (goe476-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 476 AIRFOIL (goe476-il)
Reynolds number: 500,000
Max Cl/Cd: 108.4 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe476-il-500000.txt
Download as CSV file: xf-goe476-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 476 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.2110   0.11050   0.10799  -0.0605   0.9906   0.0513
 -11.000  -0.5199   0.03707   0.03368  -0.1233   0.9575   0.0498
 -10.750  -0.5298   0.03036   0.02632  -0.1262   0.9448   0.0504
 -10.500  -0.5010   0.02873   0.02463  -0.1283   0.9383   0.0509
 -10.250  -0.4754   0.02760   0.02342  -0.1291   0.9279   0.0514
 -10.000  -0.4419   0.02687   0.02264  -0.1309   0.9196   0.0521
  -9.750  -0.4193   0.02595   0.02160  -0.1308   0.9055   0.0528
  -9.500  -0.4030   0.02442   0.01980  -0.1300   0.8903   0.0534
  -9.250  -0.3876   0.02301   0.01810  -0.1286   0.8752   0.0541
  -9.000  -0.3712   0.02184   0.01663  -0.1271   0.8612   0.0548
  -8.750  -0.3534   0.02092   0.01542  -0.1256   0.8478   0.0553
  -8.500  -0.3356   0.02024   0.01449  -0.1239   0.8349   0.0558
  -8.250  -0.3174   0.01889   0.01302  -0.1226   0.8233   0.0566
  -8.000  -0.2949   0.01844   0.01250  -0.1216   0.8116   0.0573
  -7.750  -0.2730   0.01802   0.01200  -0.1205   0.8000   0.0581
  -7.500  -0.2505   0.01759   0.01143  -0.1195   0.7895   0.0588
  -7.250  -0.2286   0.01709   0.01082  -0.1183   0.7784   0.0596
  -7.000  -0.2061   0.01662   0.01019  -0.1172   0.7680   0.0604
  -6.750  -0.1836   0.01618   0.00960  -0.1160   0.7567   0.0612
  -6.500  -0.1604   0.01585   0.00911  -0.1149   0.7464   0.0619
  -6.250  -0.1381   0.01507   0.00822  -0.1139   0.7367   0.0629
  -6.000  -0.1140   0.01468   0.00781  -0.1131   0.7284   0.0639
  -5.750  -0.0896   0.01442   0.00750  -0.1123   0.7201   0.0650
  -5.500  -0.0649   0.01413   0.00713  -0.1115   0.7129   0.0660
  -5.250  -0.0400   0.01383   0.00677  -0.1108   0.7055   0.0671
  -5.000  -0.0150   0.01359   0.00642  -0.1100   0.6988   0.0682
  -4.750   0.0107   0.01341   0.00614  -0.1094   0.6929   0.0690
  -4.500   0.0347   0.01282   0.00557  -0.1086   0.6870   0.0707
  -4.250   0.0600   0.01262   0.00534  -0.1080   0.6812   0.0721
  -4.000   0.0858   0.01246   0.00513  -0.1074   0.6758   0.0737
  -3.750   0.1113   0.01226   0.00490  -0.1067   0.6705   0.0752
  -3.500   0.1372   0.01212   0.00469  -0.1061   0.6651   0.0765
  -3.250   0.1619   0.01178   0.00434  -0.1054   0.6602   0.0786
  -3.000   0.1876   0.01163   0.00419  -0.1048   0.6557   0.0808
  -2.750   0.2134   0.01149   0.00406  -0.1042   0.6511   0.0834
  -2.500   0.2391   0.01135   0.00388  -0.1036   0.6464   0.0858
  -2.250   0.2645   0.01118   0.00371  -0.1029   0.6419   0.0892
  -2.000   0.2907   0.01110   0.00361  -0.1024   0.6375   0.0928
  -1.750   0.3158   0.01094   0.00349  -0.1017   0.6329   0.0974
  -1.500   0.3416   0.01086   0.00343  -0.1011   0.6281   0.1035
  -1.250   0.3676   0.01079   0.00338  -0.1005   0.6236   0.1115
  -1.000   0.3941   0.01077   0.00338  -0.1001   0.6193   0.1217
  -0.750   0.4198   0.01071   0.00338  -0.0994   0.6150   0.1329
  -0.500   0.4461   0.01073   0.00340  -0.0989   0.6105   0.1431
  -0.250   0.4719   0.01069   0.00339  -0.0984   0.6060   0.1530
   0.000   0.4992   0.01077   0.00341  -0.0981   0.6015   0.1606
   0.250   0.5237   0.01068   0.00340  -0.0973   0.5971   0.1688
   0.500   0.5490   0.01067   0.00339  -0.0966   0.5917   0.1754
   0.750   0.5739   0.01063   0.00335  -0.0958   0.5862   0.1837
   1.000   0.5991   0.01063   0.00336  -0.0952   0.5807   0.1912
   1.250   0.6233   0.01057   0.00335  -0.0943   0.5752   0.1993
   1.500   0.6480   0.01054   0.00335  -0.0935   0.5700   0.2093
   1.750   0.6733   0.01057   0.00336  -0.0928   0.5647   0.2224
   2.000   0.6965   0.01047   0.00339  -0.0917   0.5592   0.2428
   2.250   0.7188   0.01031   0.00342  -0.0906   0.5534   0.2973
   2.500   0.7240   0.00933   0.00351  -0.0861   0.5487   0.6836
   2.750   0.9273   0.00938   0.00413  -0.1233   0.5383   1.0000
   3.000   0.9489   0.00947   0.00416  -0.1219   0.5323   1.0000
   3.250   0.9705   0.00957   0.00422  -0.1206   0.5265   1.0000
   3.500   0.9921   0.00964   0.00429  -0.1192   0.5202   1.0000
   3.750   1.0131   0.00975   0.00435  -0.1178   0.5143   1.0000
   4.000   1.0343   0.00987   0.00444  -0.1163   0.5089   1.0000
   4.250   1.0554   0.00995   0.00454  -0.1149   0.5025   1.0000
   4.500   1.0754   0.01009   0.00462  -0.1132   0.4965   1.0000
   4.750   1.0957   0.01021   0.00473  -0.1116   0.4905   1.0000
   5.000   1.1153   0.01033   0.00485  -0.1099   0.4833   1.0000
   5.250   1.1328   0.01050   0.00496  -0.1078   0.4753   1.0000
   5.500   1.1512   0.01062   0.00508  -0.1058   0.4665   1.0000
   5.750   1.1680   0.01083   0.00522  -0.1036   0.4592   1.0000
   6.000   1.1872   0.01096   0.00538  -0.1018   0.4529   1.0000
   6.250   1.2045   0.01114   0.00554  -0.0996   0.4462   1.0000
   6.500   1.2207   0.01134   0.00572  -0.0973   0.4393   1.0000
   6.750   1.2371   0.01150   0.00590  -0.0950   0.4315   1.0000
   7.000   1.2495   0.01175   0.00609  -0.0919   0.4238   1.0000
   7.250   1.2635   0.01189   0.00626  -0.0891   0.4166   1.0000
   7.500   1.2735   0.01213   0.00646  -0.0856   0.4085   1.0000
   7.750   1.2873   0.01231   0.00667  -0.0828   0.4005   1.0000
   8.000   1.2983   0.01259   0.00692  -0.0796   0.3912   1.0000
   8.250   1.3121   0.01284   0.00718  -0.0770   0.3809   1.0000
   8.500   1.3230   0.01319   0.00750  -0.0740   0.3682   1.0000
   8.750   1.3323   0.01362   0.00788  -0.0708   0.3505   1.0000
   9.000   1.3378   0.01423   0.00839  -0.0671   0.3257   1.0000
   9.250   1.3376   0.01513   0.00913  -0.0627   0.2937   1.0000
   9.500   1.3354   0.01626   0.01009  -0.0584   0.2663   1.0000
   9.750   1.3381   0.01730   0.01104  -0.0550   0.2497   1.0000
  10.000   1.3431   0.01832   0.01201  -0.0521   0.2380   1.0000
  10.250   1.3499   0.01932   0.01298  -0.0496   0.2292   1.0000
  10.500   1.3584   0.02029   0.01394  -0.0474   0.2217   1.0000
  10.750   1.3663   0.02134   0.01498  -0.0453   0.2147   1.0000
  11.000   1.3733   0.02250   0.01615  -0.0433   0.2087   1.0000
  11.250   1.3855   0.02339   0.01708  -0.0418   0.2035   1.0000
  11.500   1.3935   0.02457   0.01827  -0.0401   0.1979   1.0000
  11.750   1.4004   0.02589   0.01958  -0.0384   0.1928   1.0000
  12.000   1.4129   0.02684   0.02060  -0.0373   0.1878   1.0000
  12.250   1.4211   0.02814   0.02191  -0.0358   0.1825   1.0000
  12.500   1.4275   0.02961   0.02339  -0.0344   0.1771   1.0000
  12.750   1.4387   0.03076   0.02459  -0.0334   0.1721   1.0000
  13.000   1.4451   0.03231   0.02615  -0.0322   0.1662   1.0000
  13.250   1.4527   0.03380   0.02767  -0.0311   0.1604   1.0000
  13.500   1.4597   0.03538   0.02928  -0.0300   0.1539   1.0000
  13.750   1.4639   0.03725   0.03115  -0.0290   0.1473   1.0000
  14.000   1.4687   0.03911   0.03301  -0.0280   0.1394   1.0000
  14.250   1.4716   0.04116   0.03507  -0.0270   0.1318   1.0000
  14.500   1.4703   0.04367   0.03756  -0.0261   0.1231   1.0000
  14.750   1.4698   0.04615   0.04003  -0.0252   0.1137   1.0000
  15.000   1.4680   0.04879   0.04265  -0.0243   0.1046   1.0000
  15.250   1.4656   0.05154   0.04539  -0.0236   0.0962   1.0000
  15.500   1.4619   0.05449   0.04832  -0.0229   0.0892   1.0000
  15.750   1.4600   0.05731   0.05115  -0.0224   0.0839   1.0000
  16.000   1.4584   0.06011   0.05397  -0.0219   0.0800   1.0000
  16.250   1.4585   0.06281   0.05670  -0.0215   0.0773   1.0000
  16.500   1.4556   0.06587   0.05978  -0.0212   0.0745   1.0000
  16.750   1.4540   0.06882   0.06277  -0.0210   0.0723   1.0000
  17.000   1.4549   0.07152   0.06554  -0.0209   0.0705   1.0000
  17.250   1.4550   0.07434   0.06840  -0.0208   0.0688   1.0000
  17.500   1.4520   0.07759   0.07168  -0.0209   0.0671   1.0000
  17.750   1.4471   0.08109   0.07521  -0.0210   0.0654   1.0000
  18.000   1.4482   0.08387   0.07806  -0.0211   0.0644   1.0000
  18.250   1.4492   0.08669   0.08096  -0.0213   0.0632   1.0000
  18.500   1.4495   0.08963   0.08396  -0.0215   0.0621   1.0000
  18.750   1.4488   0.09269   0.08708  -0.0218   0.0612   1.0000
  19.000   1.4468   0.09594   0.09038  -0.0223   0.0602   1.0000
  19.250   1.4442   0.09924   0.09371  -0.0227   0.0593   1.0000
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