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GOE 630 AIRFOIL (goe630-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 630 AIRFOIL (goe630-il)
Reynolds number: 100,000
Max Cl/Cd: 54.37 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe630-il-100000-n5.txt
Download as CSV file: xf-goe630-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250   0.0512   0.09794   0.09283  -0.0985   0.9041   0.0590
  -9.000   0.0640   0.09543   0.09027  -0.1038   0.8964   0.0610
  -8.750   0.0665   0.09392   0.08875  -0.1079   0.8841   0.0616
  -8.500   0.0697   0.09205   0.08686  -0.1117   0.8729   0.0618
  -8.250   0.0985   0.08668   0.08145  -0.1103   0.8688   0.0631
  -8.000   0.1186   0.08363   0.07834  -0.1116   0.8625   0.0653
  -7.750   0.1264   0.08159   0.07630  -0.1121   0.8521   0.0677
  -7.500   0.1340   0.07946   0.07412  -0.1140   0.8434   0.0699
  -7.250   0.1284   0.07845   0.07312  -0.1153   0.8318   0.0714
  -7.000   0.1263   0.07721   0.07185  -0.1202   0.8208   0.0722
  -6.750   0.1370   0.07440   0.06899  -0.1240   0.8131   0.0725
  -6.500   0.1488   0.07114   0.06574  -0.1204   0.8061   0.0733
  -6.250   0.1630   0.06871   0.06329  -0.1187   0.7992   0.0750
  -6.000   0.1760   0.06662   0.06115  -0.1190   0.7922   0.0777
  -5.750   0.1859   0.06470   0.05920  -0.1213   0.7836   0.0816
  -5.500   0.2065   0.06227   0.05650  -0.1327   0.7757   0.0846
  -5.250   0.2153   0.05931   0.05360  -0.1301   0.7682   0.0854
  -5.000   0.2312   0.05680   0.05106  -0.1293   0.7625   0.0865
  -4.750   0.2447   0.05479   0.04903  -0.1290   0.7549   0.0878
  -4.500   0.2630   0.05256   0.04671  -0.1301   0.7480   0.0894
  -4.000   0.3164   0.04235   0.03571  -0.1402   0.7345   0.0615
  -3.750   0.3387   0.04029   0.03355  -0.1406   0.7286   0.0606
  -3.500   0.3584   0.03817   0.03129  -0.1407   0.7210   0.0595
  -3.250   0.3825   0.03567   0.02854  -0.1415   0.7142   0.0584
  -3.000   0.4083   0.03315   0.02567  -0.1423   0.7080   0.0577
  -2.750   0.4305   0.03117   0.02339  -0.1421   0.6999   0.0584
  -2.500   0.4586   0.02912   0.02089  -0.1425   0.6941   0.0596
  -2.250   0.4800   0.02766   0.01911  -0.1417   0.6857   0.0599
  -2.000   0.5065   0.02622   0.01729  -0.1415   0.6788   0.0601
  -1.750   0.5301   0.02509   0.01583  -0.1406   0.6708   0.0606
  -1.500   0.5558   0.02410   0.01450  -0.1400   0.6631   0.0613
  -1.250   0.5803   0.02333   0.01355  -0.1394   0.6554   0.0630
  -1.000   0.6045   0.02281   0.01295  -0.1387   0.6470   0.0651
  -0.750   0.6294   0.02228   0.01227  -0.1380   0.6389   0.0671
  -0.500   0.6540   0.02173   0.01156  -0.1372   0.6303   0.0687
  -0.250   0.6786   0.02127   0.01095  -0.1363   0.6219   0.0706
   0.000   0.7032   0.02086   0.01044  -0.1355   0.6133   0.0732
   0.250   0.7264   0.02060   0.01020  -0.1347   0.6043   0.0773
   0.500   0.7517   0.02031   0.00982  -0.1340   0.5959   0.0816
   0.750   0.7749   0.02012   0.00957  -0.1330   0.5864   0.0853
   1.000   0.8004   0.01989   0.00929  -0.1324   0.5784   0.0927
   1.250   0.8226   0.01983   0.00921  -0.1313   0.5685   0.1015
   1.500   0.8497   0.01971   0.00899  -0.1310   0.5606   0.1163
   1.750   0.8737   0.01964   0.00902  -0.1304   0.5511   0.1499
   2.000   0.9004   0.01926   0.00908  -0.1304   0.5430   0.3225
   2.250   0.9411   0.01830   0.00916  -0.1332   0.5333   1.0000
   2.500   0.9644   0.01856   0.00921  -0.1323   0.5251   1.0000
   2.750   0.9871   0.01883   0.00932  -0.1313   0.5168   1.0000
   3.000   1.0104   0.01911   0.00945  -0.1305   0.5096   1.0000
   3.250   1.0324   0.01943   0.00965  -0.1295   0.5019   1.0000
   3.500   1.0566   0.01971   0.00976  -0.1289   0.4954   1.0000
   3.750   1.0771   0.02008   0.01009  -0.1277   0.4876   1.0000
   4.000   1.1008   0.02038   0.01025  -0.1270   0.4814   1.0000
   4.250   1.1215   0.02077   0.01058  -0.1258   0.4745   1.0000
   4.500   1.1432   0.02114   0.01088  -0.1249   0.4682   1.0000
   4.750   1.1678   0.02148   0.01109  -0.1244   0.4631   1.0000
   5.000   1.1869   0.02193   0.01156  -0.1231   0.4570   1.0000
   5.250   1.2085   0.02233   0.01192  -0.1222   0.4515   1.0000
   5.500   1.2334   0.02270   0.01216  -0.1218   0.4470   1.0000
   5.750   1.2507   0.02320   0.01272  -0.1203   0.4411   1.0000
   6.000   1.2711   0.02364   0.01315  -0.1192   0.4360   1.0000
   6.250   1.2952   0.02404   0.01347  -0.1188   0.4318   1.0000
   6.500   1.3141   0.02457   0.01403  -0.1176   0.4273   1.0000
   6.750   1.3321   0.02510   0.01461  -0.1162   0.4227   1.0000
   7.000   1.3527   0.02558   0.01510  -0.1153   0.4187   1.0000
   7.250   1.3776   0.02601   0.01547  -0.1150   0.4151   1.0000
   7.500   1.3922   0.02663   0.01617  -0.1132   0.4109   1.0000
   7.750   1.4067   0.02726   0.01688  -0.1114   0.4065   1.0000
   8.000   1.4257   0.02781   0.01745  -0.1103   0.4027   1.0000
   8.250   1.4493   0.02830   0.01794  -0.1099   0.3996   1.0000
   8.500   1.4684   0.02893   0.01861  -0.1089   0.3965   1.0000
   8.750   1.4782   0.02975   0.01959  -0.1066   0.3928   1.0000
   9.000   1.4919   0.03049   0.02042  -0.1048   0.3891   1.0000
   9.250   1.5104   0.03111   0.02109  -0.1038   0.3857   1.0000
   9.500   1.5347   0.03161   0.02159  -0.1036   0.3828   1.0000
   9.750   1.5466   0.03249   0.02260  -0.1018   0.3797   1.0000
  10.000   1.5507   0.03363   0.02392  -0.0991   0.3763   1.0000
  10.250   1.5601   0.03463   0.02504  -0.0971   0.3728   1.0000
  10.500   1.5760   0.03539   0.02588  -0.0959   0.3696   1.0000
  10.750   1.5991   0.03592   0.02646  -0.0956   0.3669   1.0000
  11.000   1.6108   0.03693   0.02759  -0.0941   0.3640   1.0000
  11.250   1.6014   0.03882   0.02971  -0.0904   0.3602   1.0000
  11.500   1.6021   0.04038   0.03143  -0.0880   0.3566   1.0000
  11.750   1.6144   0.04138   0.03253  -0.0867   0.3534   1.0000
  12.000   1.6385   0.04180   0.03302  -0.0865   0.3507   1.0000
  12.250   1.6391   0.04351   0.03488  -0.0843   0.3474   1.0000
  12.500   1.6106   0.04714   0.03877  -0.0804   0.3431   1.0000
  12.750   1.6033   0.04962   0.04141  -0.0782   0.3391   1.0000
  13.000   1.6258   0.04985   0.04170  -0.0778   0.3356   1.0000
  13.250   1.6321   0.05127   0.04322  -0.0765   0.3315   1.0000
  13.500   1.5451   0.06165   0.05393  -0.0724   0.3262   1.0000
  13.750   1.5327   0.06536   0.05777  -0.0714   0.3214   1.0000
  14.000   1.6046   0.05954   0.05190  -0.0714   0.3160   1.0000
  14.250   1.3635   0.09400   0.08665  -0.0733   0.2998   1.0000
  14.500   1.4088   0.09023   0.08301  -0.0718   0.3008   1.0000
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