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GOE 614 AIRFOIL (goe614-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 614 AIRFOIL (goe614-il)
Reynolds number: 200,000
Max Cl/Cd: 63.48 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe614-il-200000.txt
Download as CSV file: xf-goe614-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 614 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.2201   0.06528   0.06151  -0.1236   0.9438   0.0581
 -10.500  -0.2958   0.04878   0.04457  -0.1430   0.9280   0.0559
 -10.250  -0.3223   0.04393   0.03939  -0.1450   0.9148   0.0553
 -10.000  -0.3223   0.03876   0.03372  -0.1485   0.9088   0.0547
  -9.750  -0.3232   0.03632   0.03098  -0.1468   0.8979   0.0547
  -9.500  -0.3028   0.03329   0.02754  -0.1486   0.8932   0.0546
  -9.250  -0.2731   0.03065   0.02454  -0.1510   0.8902   0.0546
  -9.000  -0.2663   0.02928   0.02295  -0.1481   0.8787   0.0545
  -8.750  -0.2332   0.02736   0.02077  -0.1500   0.8747   0.0545
  -8.500  -0.2134   0.02614   0.01937  -0.1489   0.8662   0.0547
  -8.250  -0.1846   0.02483   0.01790  -0.1494   0.8596   0.0549
  -8.000  -0.1468   0.02348   0.01639  -0.1515   0.8553   0.0554
  -7.750  -0.1312   0.02277   0.01559  -0.1493   0.8444   0.0557
  -7.500  -0.0966   0.02172   0.01442  -0.1506   0.8384   0.0563
  -7.250  -0.0772   0.02109   0.01371  -0.1490   0.8282   0.0568
  -7.000  -0.0468   0.02025   0.01277  -0.1495   0.8208   0.0578
  -6.750  -0.0276   0.01958   0.01212  -0.1480   0.8108   0.0589
  -6.500   0.0001   0.01891   0.01140  -0.1480   0.8024   0.0603
  -6.250   0.0202   0.01845   0.01090  -0.1465   0.7920   0.0615
  -6.000   0.0479   0.01792   0.01026  -0.1464   0.7835   0.0630
  -5.750   0.0676   0.01755   0.00983  -0.1447   0.7729   0.0646
  -5.500   0.0951   0.01704   0.00925  -0.1447   0.7643   0.0674
  -5.250   0.1144   0.01673   0.00891  -0.1429   0.7531   0.0709
  -4.750   0.1621   0.01600   0.00819  -0.1411   0.7331   0.0950
  -4.500   0.1884   0.01560   0.00777  -0.1408   0.7244   0.1228
  -4.250   0.2091   0.01531   0.00760  -0.1394   0.7137   0.1515
  -4.000   0.2357   0.01523   0.00753  -0.1391   0.7045   0.1811
  -3.750   0.2599   0.01521   0.00745  -0.1381   0.6943   0.1987
  -3.500   0.2854   0.01521   0.00737  -0.1375   0.6848   0.2141
  -3.250   0.3101   0.01518   0.00728  -0.1368   0.6752   0.2282
  -3.000   0.3351   0.01520   0.00721  -0.1361   0.6661   0.2423
  -2.750   0.3601   0.01523   0.00714  -0.1354   0.6573   0.2569
  -2.500   0.3853   0.01525   0.00714  -0.1348   0.6491   0.2723
  -2.250   0.4087   0.01525   0.00712  -0.1339   0.6403   0.2856
  -2.000   0.4358   0.01530   0.00707  -0.1336   0.6328   0.2997
  -1.750   0.4580   0.01533   0.00709  -0.1324   0.6241   0.3123
  -1.500   0.4866   0.01536   0.00705  -0.1325   0.6174   0.3261
  -1.250   0.5078   0.01542   0.00713  -0.1312   0.6097   0.3404
  -1.000   0.5331   0.01548   0.00714  -0.1306   0.6029   0.3563
  -0.750   0.5607   0.01556   0.00718  -0.1305   0.5968   0.3720
  -0.500   0.5816   0.01558   0.00727  -0.1292   0.5896   0.3871
  -0.250   0.6076   0.01560   0.00728  -0.1288   0.5835   0.4040
   0.000   0.6336   0.01568   0.00735  -0.1284   0.5778   0.4237
   0.250   0.6550   0.01572   0.00748  -0.1271   0.5715   0.4455
   0.500   0.6804   0.01576   0.00754  -0.1266   0.5662   0.4719
   0.750   0.7090   0.01586   0.00764  -0.1268   0.5614   0.5021
   1.000   0.7272   0.01590   0.00783  -0.1249   0.5555   0.5334
   1.250   0.7498   0.01590   0.00794  -0.1238   0.5501   0.5697
   1.500   0.7761   0.01592   0.00803  -0.1235   0.5456   0.6141
   1.750   0.7967   0.01590   0.00824  -0.1220   0.5408   0.6705
   2.000   0.8158   0.01572   0.00840  -0.1201   0.5348   0.7706
   2.250   0.9215   0.01582   0.00853  -0.1361   0.5253   1.0000
   2.500   0.9328   0.01596   0.00867  -0.1329   0.5185   1.0000
   2.750   0.9526   0.01609   0.00868  -0.1313   0.5120   1.0000
   3.000   0.9783   0.01632   0.00875  -0.1310   0.5065   1.0000
   3.250   0.9921   0.01651   0.00895  -0.1283   0.5008   1.0000
   3.500   1.0124   0.01670   0.00908  -0.1270   0.4958   1.0000
   3.750   1.0376   0.01693   0.00919  -0.1265   0.4915   1.0000
   4.000   1.0599   0.01721   0.00942  -0.1256   0.4871   1.0000
   4.250   1.0755   0.01744   0.00967  -0.1234   0.4823   1.0000
   4.500   1.0954   0.01765   0.00984  -0.1220   0.4776   1.0000
   4.750   1.1205   0.01788   0.00996  -0.1216   0.4733   1.0000
   5.000   1.1412   0.01817   0.01024  -0.1204   0.4690   1.0000
   5.250   1.1552   0.01843   0.01053  -0.1179   0.4644   1.0000
   5.500   1.1740   0.01866   0.01074  -0.1163   0.4600   1.0000
   5.750   1.1976   0.01890   0.01090  -0.1157   0.4560   1.0000
   6.000   1.2194   0.01921   0.01118  -0.1147   0.4518   1.0000
   6.250   1.2276   0.01948   0.01152  -0.1112   0.4473   1.0000
   6.500   1.2429   0.01974   0.01178  -0.1091   0.4429   1.0000
   6.750   1.2640   0.01998   0.01197  -0.1080   0.4388   1.0000
   7.000   1.2866   0.02031   0.01225  -0.1073   0.4345   1.0000
   7.250   1.2918   0.02065   0.01268  -0.1034   0.4297   1.0000
   7.500   1.3051   0.02092   0.01296  -0.1010   0.4247   1.0000
   7.750   1.3265   0.02117   0.01314  -0.1001   0.4203   1.0000
   8.000   1.3411   0.02157   0.01356  -0.0981   0.4159   1.0000
   8.250   1.3484   0.02200   0.01407  -0.0950   0.4109   1.0000
   8.500   1.3629   0.02234   0.01442  -0.0930   0.4063   1.0000
   8.750   1.3871   0.02261   0.01459  -0.0927   0.4018   1.0000
   9.000   1.3916   0.02319   0.01529  -0.0893   0.3970   1.0000
   9.250   1.4000   0.02372   0.01587  -0.0866   0.3919   1.0000
   9.500   1.4150   0.02411   0.01624  -0.0850   0.3871   1.0000
   9.750   1.4317   0.02456   0.01667  -0.0837   0.3825   1.0000
  10.000   1.4338   0.02534   0.01757  -0.0803   0.3771   1.0000
  10.250   1.4439   0.02593   0.01819  -0.0782   0.3720   1.0000
  10.500   1.4656   0.02627   0.01843  -0.0777   0.3677   1.0000
  10.750   1.4651   0.02730   0.01962  -0.0744   0.3623   1.0000
  11.000   1.4720   0.02815   0.02053  -0.0722   0.3573   1.0000
  11.250   1.4866   0.02874   0.02110  -0.0710   0.3530   1.0000
  11.500   1.4980   0.02954   0.02192  -0.0694   0.3485   1.0000
  11.750   1.5002   0.03074   0.02325  -0.0670   0.3436   1.0000
  12.000   1.5083   0.03170   0.02424  -0.0653   0.3389   1.0000
  12.250   1.5269   0.03218   0.02464  -0.0646   0.3347   1.0000
  12.500   1.5255   0.03375   0.02636  -0.0622   0.3300   1.0000
  12.750   1.5294   0.03509   0.02781  -0.0604   0.3255   1.0000
  13.000   1.5399   0.03608   0.02881  -0.0592   0.3217   1.0000
  13.250   1.5573   0.03669   0.02937  -0.0586   0.3179   1.0000
  13.500   1.5536   0.03869   0.03154  -0.0565   0.3137   1.0000
  13.750   1.5550   0.04040   0.03334  -0.0550   0.3091   1.0000
  14.000   1.5647   0.04151   0.03446  -0.0540   0.3050   1.0000
  14.250   1.5704   0.04299   0.03597  -0.0529   0.3005   1.0000
  14.500   1.5657   0.04539   0.03852  -0.0514   0.2959   1.0000
  14.750   1.5677   0.04728   0.04046  -0.0503   0.2913   1.0000
  15.000   1.5814   0.04812   0.04123  -0.0497   0.2865   1.0000
  15.250   1.5687   0.05152   0.04483  -0.0484   0.2815   1.0000
  15.500   1.5656   0.05408   0.04745  -0.0475   0.2762   1.0000
  15.750   1.5788   0.05503   0.04834  -0.0470   0.2719   1.0000
  16.000   1.5689   0.05846   0.05195  -0.0462   0.2675   1.0000
  16.250   1.5617   0.06172   0.05533  -0.0457   0.2626   1.0000
  16.500   1.5685   0.06341   0.05700  -0.0452   0.2579   1.0000
  16.750   1.5644   0.06641   0.06010  -0.0449   0.2533   1.0000
  17.000   1.5526   0.07042   0.06425  -0.0447   0.2483   1.0000
  17.250   1.5558   0.07259   0.06642  -0.0444   0.2430   1.0000
  17.500   1.5475   0.07627   0.07020  -0.0444   0.2375   1.0000
  17.750   1.5341   0.08071   0.07477  -0.0446   0.2320   1.0000
  18.000   1.5439   0.08207   0.07602  -0.0444   0.2259   1.0000
  18.250   1.5192   0.08812   0.08231  -0.0450   0.2199   1.0000
  18.500   1.5153   0.09140   0.08560  -0.0453   0.2135   1.0000
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