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GOE 388 AIRFOIL (goe388-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 388 AIRFOIL (goe388-il)
Reynolds number: 200,000
Max Cl/Cd: 34.67 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe388-il-200000.txt
Download as CSV file: xf-goe388-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 388 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2090   0.09320   0.08995  -0.0539   0.9453   0.0495
  -9.250  -0.3282   0.10247   0.09919  -0.0428   1.0000   0.0464
  -9.000  -0.3102   0.09882   0.09553  -0.0443   0.9909   0.0478
  -8.750  -0.2905   0.09487   0.09153  -0.0486   0.9669   0.0495
  -8.500  -0.2733   0.09102   0.08762  -0.0531   0.9386   0.0516
  -8.250  -0.2630   0.08772   0.08429  -0.0568   0.9230   0.0539
  -8.000  -0.2562   0.08522   0.08176  -0.0675   0.9050   0.0566
  -7.750  -0.2374   0.08139   0.07785  -0.0790   0.8908   0.0572
  -7.500  -0.2344   0.07510   0.07156  -0.0786   0.8814   0.0583
  -7.250  -0.2239   0.07227   0.06871  -0.0762   0.8730   0.0593
  -7.000  -0.2115   0.06969   0.06607  -0.0758   0.8562   0.0605
  -6.750  -0.1965   0.06688   0.06321  -0.0775   0.8449   0.0621
  -6.500  -0.1791   0.06373   0.06001  -0.0809   0.8356   0.0644
  -6.250  -0.1340   0.05871   0.05458  -0.0992   0.8232   0.0717
  -6.000  -0.1215   0.05271   0.04856  -0.1016   0.8162   0.0732
  -5.750  -0.1061   0.05042   0.04631  -0.1007   0.8131   0.0745
  -5.500  -0.0867   0.04824   0.04412  -0.1012   0.8118   0.0764
  -5.250  -0.0650   0.04577   0.04151  -0.1028   0.7957   0.0795
  -5.000  -0.0283   0.04049   0.03562  -0.1111   0.7797   0.0889
  -4.750  -0.0096   0.03843   0.03355  -0.1106   0.7654   0.0907
  -4.500   0.0142   0.03668   0.03185  -0.1114   0.7742   0.0939
  -4.250   0.0457   0.03368   0.02856  -0.1152   0.7797   0.1057
  -4.000   0.0688   0.03226   0.02722  -0.1153   0.7816   0.1095
  -3.750   0.0974   0.03017   0.02480  -0.1172   0.7752   0.1219
  -3.500   0.1206   0.02883   0.02337  -0.1170   0.7596   0.1266
  -3.250   0.1466   0.02724   0.02149  -0.1176   0.7428   0.1394
  -3.000   0.1726   0.02601   0.01997  -0.1180   0.7254   0.1541
  -2.750   0.2174   0.01882   0.01107  -0.1190   0.7178   0.0729
  -2.500   0.2440   0.01757   0.00954  -0.1190   0.7031   0.0734
  -2.250   0.2710   0.01668   0.00841  -0.1188   0.6888   0.0734
  -2.000   0.2980   0.01607   0.00761  -0.1186   0.6730   0.0727
  -1.750   0.3248   0.01531   0.00669  -0.1184   0.6544   0.0727
  -1.500   0.3508   0.01452   0.00574  -0.1180   0.6249   0.0735
  -1.250   0.3740   0.01410   0.00499  -0.1171   0.5649   0.0750
  -1.000   0.3964   0.01401   0.00458  -0.1162   0.5091   0.0770
  -0.750   0.4187   0.01411   0.00436  -0.1154   0.4402   0.0799
  -0.500   0.4273   0.01612   0.00491  -0.1129   0.1121   0.0835
  -0.250   0.4520   0.01622   0.00485  -0.1125   0.0670   0.0876
   0.000   0.4762   0.01626   0.00507  -0.1120   0.0625   0.0946
   0.500   0.5188   0.01680   0.00664  -0.1106   0.0515   0.3222
   0.750   0.5316   0.01621   0.00745  -0.1077   0.0491   1.0000
   1.000   0.5558   0.01659   0.00770  -0.1072   0.0463   1.0000
   1.250   0.5749   0.01776   0.00862  -0.1060   0.0450   1.0000
   1.500   0.6019   0.01765   0.00850  -0.1060   0.0432   1.0000
   1.750   0.6239   0.01840   0.00910  -0.1053   0.0419   1.0000
   2.000   0.6457   0.02009   0.01043  -0.1046   0.0409   1.0000
   2.250   0.6702   0.02048   0.01076  -0.1043   0.0405   1.0000
   2.500   0.6943   0.02034   0.01069  -0.1038   0.0398   1.0000
   2.750   0.7184   0.02078   0.01109  -0.1035   0.0391   1.0000
   3.000   0.7427   0.02142   0.01164  -0.1031   0.0384   1.0000
   3.250   0.7676   0.02219   0.01230  -0.1030   0.0379   1.0000
   3.500   0.7935   0.02310   0.01310  -0.1030   0.0374   1.0000
   3.750   0.8214   0.02425   0.01408  -0.1033   0.0370   1.0000
   4.000   0.8524   0.02586   0.01545  -0.1043   0.0367   1.0000
   4.250   0.8884   0.02851   0.01773  -0.1063   0.0364   1.0000
   4.500   0.9156   0.02965   0.01882  -0.1066   0.0363   1.0000
   4.750   0.9400   0.03016   0.01935  -0.1063   0.0363   1.0000
   5.000   0.9642   0.03068   0.01992  -0.1060   0.0363   1.0000
   5.250   0.9884   0.03124   0.02053  -0.1057   0.0362   1.0000
   5.500   1.0125   0.03184   0.02121  -0.1055   0.0362   1.0000
   5.750   1.0367   0.03251   0.02194  -0.1052   0.0361   1.0000
   6.000   1.0606   0.03322   0.02272  -0.1049   0.0360   1.0000
   6.250   1.0846   0.03398   0.02356  -0.1046   0.0360   1.0000
   6.500   1.1084   0.03480   0.02448  -0.1043   0.0359   1.0000
   6.750   1.1319   0.03566   0.02544  -0.1040   0.0358   1.0000
   7.000   1.1544   0.03644   0.02633  -0.1035   0.0356   1.0000
   7.250   1.1764   0.03728   0.02732  -0.1029   0.0352   1.0000
   7.500   1.1985   0.03834   0.02853  -0.1023   0.0348   1.0000
   7.750   1.2206   0.03965   0.02999  -0.1018   0.0340   1.0000
   8.000   1.2468   0.04216   0.03254  -0.1022   0.0329   1.0000
   8.500   1.2876   0.04646   0.03729  -0.1005   0.0315   1.0000
   8.750   1.3007   0.04768   0.03891  -0.0982   0.0291   1.0000
   9.000   1.3330   0.05669   0.04781  -0.1002   0.0278   1.0000
   9.250   1.3261   0.05323   0.04519  -0.0937   0.0268   1.0000
   9.500   1.3372   0.05580   0.04806  -0.0916   0.0253   1.0000
   9.750   1.3569   0.06147   0.05377  -0.0917   0.0244   1.0000
  10.000   1.3821   0.07046   0.06268  -0.0930   0.0240   1.0000
  10.250   1.3706   0.06952   0.06238  -0.0872   0.0239   1.0000
  10.500   1.3617   0.06952   0.06288  -0.0820   0.0236   1.0000
  10.750   1.3564   0.07075   0.06447  -0.0779   0.0231   1.0000
  11.000   1.3517   0.07319   0.06722  -0.0744   0.0226   1.0000
  11.250   1.3449   0.07605   0.07032  -0.0711   0.0221   1.0000
  11.500   1.3350   0.07900   0.07348  -0.0678   0.0218   1.0000
  11.750   1.3204   0.08179   0.07645  -0.0641   0.0216   1.0000
  12.000   1.3038   0.08472   0.07956  -0.0607   0.0215   1.0000
  12.250   1.2858   0.08794   0.08295  -0.0580   0.0214   1.0000
  12.500   1.2669   0.09142   0.08660  -0.0560   0.0213   1.0000
  12.750   1.2470   0.09522   0.09057  -0.0547   0.0213   1.0000
  13.000   1.2264   0.09937   0.09488  -0.0541   0.0212   1.0000
  13.250   1.2053   0.10391   0.09958  -0.0543   0.0212   1.0000
  13.500   1.1835   0.10882   0.10464  -0.0552   0.0212   1.0000
  13.750   1.1616   0.11421   0.11019  -0.0570   0.0213   1.0000
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