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GOE 630 AIRFOIL (goe630-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 630 AIRFOIL (goe630-il)
Reynolds number: 200,000
Max Cl/Cd: 74.88 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe630-il-200000.txt
Download as CSV file: xf-goe630-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 630 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.0118   0.10754   0.10405  -0.0856   0.9575   0.0425
 -10.000   0.0027   0.10476   0.10125  -0.0926   0.9504   0.0446
  -9.750   0.0142   0.10183   0.09831  -0.1025   0.9438   0.0451
  -9.500   0.0463   0.09602   0.09247  -0.1026   0.9419   0.0457
  -9.250   0.0688   0.09242   0.08884  -0.1052   0.9347   0.0466
  -9.000   0.0927   0.08890   0.08528  -0.1097   0.9283   0.0480
  -8.750   0.1136   0.08568   0.08201  -0.1142   0.9195   0.0496
  -8.500   0.1255   0.08354   0.07981  -0.1217   0.9070   0.0519
  -8.250   0.1160   0.08269   0.07891  -0.1268   0.8889   0.0523
  -8.000   0.1431   0.07763   0.07383  -0.1250   0.8837   0.0530
  -7.750   0.1629   0.07470   0.07083  -0.1254   0.8761   0.0537
  -7.500   0.1714   0.07271   0.06881  -0.1248   0.8655   0.0548
  -7.250   0.1803   0.07065   0.06670  -0.1254   0.8567   0.0559
  -7.000   0.1822   0.06896   0.06500  -0.1249   0.8462   0.0571
  -6.750   0.1836   0.06732   0.06334  -0.1255   0.8373   0.0588
  -6.500   0.1849   0.06571   0.06157  -0.1377   0.8258   0.0610
  -6.250   0.1921   0.06231   0.05823  -0.1345   0.8188   0.0617
  -6.000   0.2051   0.06012   0.05602  -0.1319   0.8122   0.0625
  -5.750   0.2194   0.05814   0.05400  -0.1315   0.8059   0.0638
  -5.500   0.2315   0.05619   0.05203  -0.1320   0.7977   0.0654
  -5.250   0.2499   0.05377   0.04950  -0.1349   0.7916   0.0682
  -5.000   0.2719   0.04985   0.04535  -0.1437   0.7827   0.0721
  -4.750   0.2868   0.04774   0.04324  -0.1422   0.7767   0.0730
  -4.500   0.3021   0.04612   0.04160  -0.1412   0.7697   0.0745
  -4.250   0.3211   0.04441   0.03983  -0.1415   0.7624   0.0775
  -4.000   0.3534   0.04079   0.03579  -0.1475   0.7566   0.0848
  -3.750   0.3683   0.03914   0.03422  -0.1461   0.7484   0.0861
  -3.500   0.3903   0.03757   0.03256  -0.1461   0.7423   0.0886
  -3.250   0.4194   0.03544   0.02998  -0.1487   0.7348   0.0985
  -3.000   0.4387   0.03344   0.02802  -0.1481   0.7277   0.1003
  -2.750   0.4606   0.03213   0.02667  -0.1477   0.7211   0.1035
  -2.500   0.4863   0.03049   0.02470  -0.1483   0.7131   0.1150
  -2.000   0.5331   0.02797   0.02193  -0.1477   0.6981   0.1318
  -1.750   0.5574   0.02666   0.02057  -0.1475   0.6915   0.1363
  -1.500   0.5905   0.02211   0.01484  -0.1466   0.6843   0.0828
  -1.250   0.6154   0.02033   0.01284  -0.1460   0.6767   0.0795
  -1.000   0.6404   0.01933   0.01159  -0.1452   0.6685   0.0793
  -0.750   0.6663   0.01835   0.01034  -0.1444   0.6602   0.0783
  -0.500   0.6916   0.01762   0.00941  -0.1436   0.6516   0.0782
  -0.250   0.7176   0.01703   0.00864  -0.1429   0.6431   0.0792
   0.000   0.7423   0.01666   0.00816  -0.1420   0.6336   0.0818
   0.250   0.7687   0.01619   0.00753  -0.1414   0.6251   0.0848
   0.500   0.7915   0.01576   0.00715  -0.1403   0.6145   0.0881
   0.750   0.8168   0.01549   0.00682  -0.1396   0.6054   0.0925
   1.000   0.8403   0.01528   0.00656  -0.1386   0.5951   0.0989
   1.250   0.8638   0.01509   0.00640  -0.1376   0.5852   0.1084
   1.500   0.8886   0.01491   0.00617  -0.1369   0.5763   0.1231
   1.750   0.9102   0.01467   0.00616  -0.1356   0.5657   0.1826
   2.000   0.9632   0.01327   0.00624  -0.1413   0.5547   1.0000
   2.250   0.9872   0.01347   0.00625  -0.1404   0.5451   1.0000
   2.500   1.0101   0.01371   0.00638  -0.1395   0.5353   1.0000
   2.750   1.0353   0.01397   0.00643  -0.1389   0.5272   1.0000
   3.000   1.0572   0.01422   0.00663  -0.1378   0.5180   1.0000
   3.250   1.0828   0.01452   0.00674  -0.1374   0.5106   1.0000
   3.500   1.1042   0.01478   0.00699  -0.1362   0.5021   1.0000
   3.750   1.1294   0.01509   0.00714  -0.1358   0.4950   1.0000
   4.000   1.1509   0.01538   0.00742  -0.1347   0.4872   1.0000
   4.250   1.1749   0.01569   0.00762  -0.1340   0.4804   1.0000
   4.500   1.1982   0.01603   0.00792  -0.1333   0.4740   1.0000
   4.750   1.2208   0.01635   0.00821  -0.1325   0.4677   1.0000
   5.000   1.2472   0.01673   0.00845  -0.1324   0.4624   1.0000
   5.250   1.2682   0.01707   0.00883  -0.1312   0.4566   1.0000
   5.500   1.2909   0.01741   0.00915  -0.1305   0.4511   1.0000
   5.750   1.3176   0.01781   0.00944  -0.1305   0.4462   1.0000
   6.000   1.3377   0.01818   0.00987  -0.1293   0.4410   1.0000
   6.250   1.3597   0.01854   0.01024  -0.1284   0.4360   1.0000
   6.500   1.3847   0.01893   0.01059  -0.1281   0.4318   1.0000
   6.750   1.4102   0.01941   0.01103  -0.1280   0.4278   1.0000
   7.000   1.4294   0.01981   0.01153  -0.1267   0.4235   1.0000
   7.250   1.4516   0.02022   0.01197  -0.1259   0.4193   1.0000
   7.500   1.4769   0.02063   0.01234  -0.1258   0.4155   1.0000
   7.750   1.5022   0.02115   0.01285  -0.1257   0.4118   1.0000
   8.000   1.5193   0.02161   0.01343  -0.1241   0.4080   1.0000
   8.250   1.5400   0.02207   0.01397  -0.1231   0.4043   1.0000
   8.500   1.5639   0.02252   0.01443  -0.1228   0.4010   1.0000
   8.750   1.5926   0.02303   0.01490  -0.1233   0.3978   1.0000
   9.000   1.6101   0.02361   0.01560  -0.1219   0.3944   1.0000
   9.250   1.6256   0.02414   0.01628  -0.1202   0.3910   1.0000
   9.500   1.6450   0.02465   0.01687  -0.1191   0.3876   1.0000
   9.750   1.6687   0.02510   0.01732  -0.1188   0.3842   1.0000
  10.000   1.6951   0.02561   0.01782  -0.1190   0.3799   1.0000
  10.250   1.6986   0.02613   0.01853  -0.1152   0.3756   1.0000
  10.500   1.7093   0.02647   0.01894  -0.1125   0.3706   1.0000
  10.750   1.7383   0.02671   0.01905  -0.1131   0.3650   1.0000
  11.000   1.7344   0.02730   0.01986  -0.1081   0.3611   1.0000
  11.250   1.7382   0.02784   0.02052  -0.1046   0.3566   1.0000
  11.500   1.7534   0.02811   0.02079  -0.1029   0.3515   1.0000
  11.750   1.7631   0.02869   0.02143  -0.1005   0.3467   1.0000
  12.000   1.7593   0.02949   0.02239  -0.0964   0.3418   1.0000
  12.250   1.7674   0.02997   0.02292  -0.0940   0.3365   1.0000
  12.500   1.7745   0.03065   0.02364  -0.0916   0.3310   1.0000
  12.750   1.7696   0.03180   0.02497  -0.0880   0.3260   1.0000
  13.000   1.7751   0.03258   0.02581  -0.0858   0.3206   1.0000
  13.250   1.7769   0.03365   0.02694  -0.0833   0.3148   1.0000
  13.500   1.7702   0.03523   0.02870  -0.0803   0.3088   1.0000
  13.750   1.7778   0.03609   0.02952  -0.0786   0.3025   1.0000
  14.000   1.7676   0.03825   0.03192  -0.0759   0.2967   1.0000
  14.250   1.7629   0.04008   0.03382  -0.0737   0.2892   1.0000
  14.500   1.7542   0.04249   0.03638  -0.0717   0.2813   1.0000
  14.750   1.7489   0.04475   0.03867  -0.0701   0.2725   1.0000
  15.000   1.7361   0.04803   0.04213  -0.0685   0.2621   1.0000
  15.250   1.7242   0.05146   0.04565  -0.0673   0.2503   1.0000
  15.500   1.7098   0.05540   0.04966  -0.0664   0.2364   1.0000
  15.750   1.6924   0.05991   0.05421  -0.0657   0.2197   1.0000
  16.000   1.6682   0.06548   0.05974  -0.0653   0.1995   1.0000
  16.250   1.6433   0.07141   0.06564  -0.0652   0.1804   1.0000
  16.500   1.6150   0.07803   0.07222  -0.0655   0.1634   1.0000
  16.750   1.5854   0.08511   0.07927  -0.0662   0.1473   1.0000
  17.000   1.5572   0.09223   0.08637  -0.0672   0.1308   1.0000
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