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GOE 394 AIRFOIL (goe394-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 394 AIRFOIL (goe394-il)
Reynolds number: 100,000
Max Cl/Cd: 64.42 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe394-il-100000.txt
Download as CSV file: xf-goe394-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 394 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.2844   0.09706   0.09251  -0.0246   1.0000   0.0701
  -7.250  -0.2845   0.09542   0.09098  -0.0249   1.0000   0.0723
  -7.000  -0.3024   0.09558   0.09128  -0.0214   1.0000   0.0731
  -6.750  -0.3253   0.09614   0.09194  -0.0169   1.0000   0.0733
  -6.500  -0.3398   0.09632   0.09220  -0.0155   1.0000   0.0743
  -6.250  -0.3460   0.09728   0.09319  -0.0194   1.0000   0.0753
  -6.000  -0.3313   0.09404   0.08995  -0.0255   0.9976   0.0762
  -5.750  -0.3240   0.08860   0.08453  -0.0209   0.9956   0.0776
  -5.500  -0.3055   0.08488   0.08079  -0.0230   0.9921   0.0800
  -5.250  -0.2807   0.08144   0.07731  -0.0282   0.9875   0.0835
  -5.000  -0.2144   0.07891   0.07454  -0.0513   0.9813   0.0884
  -4.750  -0.2137   0.07410   0.06981  -0.0460   0.9781   0.0897
  -4.500  -0.1955   0.07060   0.06629  -0.0464   0.9742   0.0927
  -4.250  -0.1076   0.06814   0.06336  -0.0707   0.9678   0.1012
  -4.000  -0.0969   0.06279   0.05814  -0.0685   0.9617   0.1023
  -3.750  -0.0664   0.05875   0.05411  -0.0705   0.9567   0.1060
  -3.500  -0.0049   0.05553   0.05054  -0.0839   0.9489   0.1152
  -3.250   0.0208   0.05184   0.04689  -0.0849   0.9440   0.1177
  -3.000   0.0864   0.04880   0.04346  -0.0968   0.9397   0.1288
  -2.750   0.1014   0.04603   0.04078  -0.0957   0.9329   0.1314
  -2.500   0.1506   0.04323   0.03777  -0.1023   0.9286   0.1449
  -2.250   0.1985   0.04082   0.03513  -0.1082   0.9243   0.1589
  -2.000   0.2215   0.03885   0.03319  -0.1084   0.9171   0.1653
  -1.750   0.2739   0.03655   0.03064  -0.1146   0.9130   0.1897
  -1.500   0.3041   0.03485   0.02893  -0.1159   0.9066   0.2080
  -1.250   0.3377   0.03344   0.02746  -0.1178   0.9000   0.2496
  -1.000   0.4191   0.02753   0.02013  -0.1270   0.8972   0.1233
  -0.750   0.4517   0.02588   0.01808  -0.1277   0.8894   0.1218
  -0.500   0.4905   0.02447   0.01636  -0.1292   0.8832   0.1328
  -0.250   0.5216   0.02343   0.01510  -0.1295   0.8750   0.1480
   0.000   0.5561   0.02256   0.01397  -0.1299   0.8678   0.1729
   0.250   0.5821   0.02223   0.01376  -0.1295   0.8579   0.1975
   0.500   0.6149   0.02164   0.01310  -0.1294   0.8508   0.2146
   0.750   0.6406   0.02132   0.01275  -0.1285   0.8394   0.2214
   1.000   0.6680   0.02097   0.01238  -0.1276   0.8291   0.2256
   1.250   0.6973   0.02050   0.01184  -0.1266   0.8205   0.2304
   1.500   0.7226   0.02024   0.01164  -0.1254   0.8079   0.2378
   1.750   0.7486   0.02002   0.01141  -0.1241   0.7954   0.2459
   2.000   0.7746   0.01973   0.01118  -0.1228   0.7832   0.2535
   2.250   0.8007   0.01943   0.01091  -0.1213   0.7713   0.2649
   2.500   0.8269   0.01912   0.01065  -0.1198   0.7593   0.2849
   2.750   0.8514   0.01857   0.01073  -0.1186   0.7449   0.4413
   3.000   0.8779   0.01785   0.01051  -0.1172   0.7302   1.0000
   3.250   0.9031   0.01796   0.01049  -0.1159   0.7152   1.0000
   3.500   0.9283   0.01808   0.01052  -0.1146   0.7001   1.0000
   3.750   0.9535   0.01819   0.01060  -0.1135   0.6849   1.0000
   4.000   0.9788   0.01829   0.01067  -0.1125   0.6698   1.0000
   4.250   1.0042   0.01833   0.01069  -0.1114   0.6546   1.0000
   4.500   1.0298   0.01827   0.01061  -0.1104   0.6392   1.0000
   4.750   1.0553   0.01815   0.01051  -0.1092   0.6231   1.0000
   5.000   1.0802   0.01811   0.01050  -0.1082   0.6051   1.0000
   5.250   1.1056   0.01806   0.01045  -0.1072   0.5882   1.0000
   5.500   1.1311   0.01804   0.01041  -0.1061   0.5712   1.0000
   5.750   1.1564   0.01811   0.01044  -0.1050   0.5538   1.0000
   6.000   1.1815   0.01834   0.01060  -0.1040   0.5368   1.0000
   6.250   1.2061   0.01875   0.01101  -0.1031   0.5198   1.0000
   6.500   1.2304   0.01924   0.01156  -0.1023   0.5027   1.0000
   6.750   1.2542   0.01975   0.01213  -0.1014   0.4850   1.0000
   7.000   1.2775   0.02026   0.01268  -0.1003   0.4658   1.0000
   7.250   1.2993   0.02071   0.01316  -0.0990   0.4423   1.0000
   7.500   1.3174   0.02101   0.01349  -0.0971   0.4084   1.0000
   7.750   1.3336   0.02134   0.01383  -0.0951   0.3679   1.0000
   8.000   1.3488   0.02189   0.01440  -0.0931   0.3204   1.0000
   8.250   1.3601   0.02297   0.01521  -0.0908   0.2540   1.0000
   8.500   1.3650   0.02496   0.01666  -0.0881   0.1833   1.0000
   8.750   1.3637   0.02773   0.01893  -0.0848   0.1319   1.0000
   9.000   1.3595   0.03070   0.02157  -0.0811   0.0999   1.0000
   9.250   1.3604   0.03316   0.02385  -0.0778   0.0841   1.0000
   9.500   1.3673   0.03494   0.02569  -0.0751   0.0738   1.0000
   9.750   1.3764   0.03684   0.02764  -0.0727   0.0664   1.0000
  10.000   1.3875   0.03880   0.02951  -0.0707   0.0612   1.0000
  10.250   1.4093   0.04117   0.03198  -0.0694   0.0574   1.0000
  10.500   1.4272   0.04330   0.03427  -0.0680   0.0538   1.0000
  10.750   1.4471   0.04580   0.03670  -0.0673   0.0501   1.0000
  11.000   1.4692   0.04931   0.04052  -0.0666   0.0482   1.0000
  11.250   1.4809   0.05251   0.04410  -0.0648   0.0474   1.0000
  11.500   1.4859   0.05592   0.04791  -0.0625   0.0469   1.0000
  11.750   1.4846   0.05946   0.05183  -0.0598   0.0466   1.0000
  12.000   1.4774   0.06301   0.05573  -0.0571   0.0464   1.0000
  12.250   1.4658   0.06670   0.05975  -0.0546   0.0462   1.0000
  12.500   1.4512   0.07067   0.06403  -0.0526   0.0461   1.0000
  12.750   1.4341   0.07500   0.06867  -0.0513   0.0461   1.0000
  13.000   1.4147   0.07980   0.07374  -0.0507   0.0462   1.0000
  13.250   1.3935   0.08506   0.07927  -0.0508   0.0464   1.0000
  13.500   1.3708   0.09085   0.08530  -0.0518   0.0467   1.0000
  13.750   1.3471   0.09719   0.09186  -0.0537   0.0470   1.0000
  14.000   1.3233   0.10410   0.09896  -0.0563   0.0475   1.0000
  14.250   1.2998   0.11155   0.10657  -0.0598   0.0480   1.0000
  14.500   1.2774   0.11952   0.11468  -0.0640   0.0486   1.0000
  14.750   1.2585   0.12772   0.12298  -0.0682   0.0491   1.0000
  15.000   1.1147   0.18748   0.18280  -0.1116   0.0895   1.0000
  15.250   1.1475   0.18399   0.17947  -0.1024   0.0846   1.0000
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