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GOE 567 AIRFOIL (goe567-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 567 AIRFOIL (goe567-il)
Reynolds number: 100,000
Max Cl/Cd: 49.7 at α=10.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe567-il-100000.txt
Download as CSV file: xf-goe567-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 567 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3076   0.12056   0.11592  -0.0336   1.0000   0.1489
  -9.750  -0.3299   0.12081   0.11627  -0.0307   1.0000   0.1523
  -9.500  -0.3377   0.11699   0.11248  -0.0387   0.9942   0.1567
  -9.250  -0.2930   0.11267   0.10808  -0.0389   0.9910   0.1628
  -9.000  -0.3244   0.11095   0.10644  -0.0525   0.9792   0.1715
  -8.750  -0.2629   0.10474   0.10009  -0.0494   0.9790   0.1755
  -8.500  -0.2474   0.10185   0.09717  -0.0544   0.9719   0.1853
  -8.250  -0.2370   0.09765   0.09297  -0.0591   0.9648   0.1901
  -8.000  -0.2049   0.09430   0.08955  -0.0610   0.9594   0.1958
  -7.750  -0.2356   0.09216   0.08750  -0.0690   0.9445   0.2047
  -7.500  -0.1750   0.08778   0.08299  -0.0683   0.9446   0.2104
  -7.250  -0.3160   0.05641   0.05121  -0.1061   0.9143   0.1408
  -7.000  -0.2932   0.04947   0.04389  -0.1133   0.9088   0.1381
  -6.750  -0.2839   0.04434   0.03828  -0.1167   0.8992   0.1381
  -6.500  -0.2530   0.03954   0.03270  -0.1223   0.8936   0.1396
  -6.250  -0.2115   0.03605   0.02885  -0.1271   0.8908   0.1420
  -6.000  -0.1986   0.03527   0.02806  -0.1253   0.8803   0.1445
  -5.750  -0.1568   0.03345   0.02598  -0.1287   0.8765   0.1489
  -5.500  -0.1267   0.03187   0.02400  -0.1301   0.8701   0.1519
  -5.250  -0.0964   0.03071   0.02235  -0.1312   0.8629   0.1556
  -5.000  -0.0521   0.02915   0.02085  -0.1344   0.8598   0.1611
  -4.750  -0.0211   0.02834   0.01986  -0.1352   0.8536   0.1658
  -4.500   0.0084   0.02765   0.01888  -0.1356   0.8462   0.1711
  -4.250   0.0505   0.02651   0.01785  -0.1381   0.8428   0.1788
  -4.000   0.0747   0.02617   0.01735  -0.1375   0.8348   0.1857
  -3.750   0.1076   0.02543   0.01669  -0.1383   0.8288   0.1941
  -3.500   0.1494   0.02455   0.01581  -0.1405   0.8253   0.2089
  -3.250   0.1679   0.02448   0.01577  -0.1390   0.8159   0.2229
  -3.000   0.2034   0.02380   0.01524  -0.1402   0.8108   0.2519
  -2.750   0.2434   0.02313   0.01487  -0.1418   0.8073   0.3109
  -2.500   0.2574   0.02365   0.01552  -0.1396   0.7967   0.3517
  -2.250   0.2940   0.02358   0.01546  -0.1404   0.7922   0.3928
  -2.000   0.3154   0.02402   0.01596  -0.1391   0.7843   0.4170
  -1.750   0.3440   0.02420   0.01609  -0.1389   0.7775   0.4435
  -1.500   0.3808   0.02405   0.01595  -0.1396   0.7736   0.4664
  -1.250   0.3941   0.02470   0.01664  -0.1373   0.7635   0.4830
  -1.000   0.4264   0.02470   0.01665  -0.1374   0.7586   0.5060
  -0.750   0.4635   0.02454   0.01646  -0.1381   0.7552   0.5330
  -0.500   0.4719   0.02535   0.01733  -0.1352   0.7441   0.5495
  -0.250   0.5061   0.02510   0.01709  -0.1355   0.7400   0.5697
   0.000   0.5200   0.02574   0.01776  -0.1336   0.7311   0.5849
   0.250   0.5494   0.02565   0.01766  -0.1336   0.7255   0.6017
   0.500   0.5860   0.02527   0.01725  -0.1344   0.7219   0.6197
   0.750   0.5942   0.02619   0.01821  -0.1319   0.7117   0.6336
   1.000   0.6264   0.02597   0.01799  -0.1322   0.7072   0.6513
   1.250   0.6631   0.02556   0.01758  -0.1331   0.7040   0.6703
   1.500   0.6660   0.02669   0.01881  -0.1299   0.6931   0.6850
   1.750   0.6998   0.02635   0.01849  -0.1303   0.6892   0.7056
   2.000   0.7161   0.02698   0.01920  -0.1288   0.6822   0.7253
   2.250   0.7354   0.02736   0.01967  -0.1276   0.6751   0.7491
   2.500   0.7709   0.02682   0.01923  -0.1281   0.6717   0.7825
   2.750   0.7715   0.02792   0.02063  -0.1244   0.6627   0.8282
   3.000   0.8082   0.02785   0.02067  -0.1261   0.6574   1.0000
   3.250   0.8539   0.02756   0.02021  -0.1289   0.6543   1.0000
   3.500   0.8530   0.02954   0.02221  -0.1261   0.6439   1.0000
   3.750   0.8906   0.02938   0.02194  -0.1274   0.6397   1.0000
   4.000   0.9379   0.02863   0.02108  -0.1295   0.6367   1.0000
   4.250   0.9296   0.03082   0.02333  -0.1254   0.6253   1.0000
   4.500   0.9761   0.02995   0.02237  -0.1273   0.6218   1.0000
   4.750   0.9789   0.03155   0.02400  -0.1244   0.6126   1.0000
   5.000   1.0146   0.03117   0.02360  -0.1249   0.6072   1.0000
   5.250   1.0628   0.03018   0.02255  -0.1270   0.6040   1.0000
   5.500   1.0529   0.03241   0.02487  -0.1225   0.5932   1.0000
   5.750   1.0985   0.03148   0.02392  -0.1242   0.5893   1.0000
   6.000   1.1450   0.03052   0.02292  -0.1259   0.5853   1.0000
   6.250   1.1413   0.03220   0.02470  -0.1220   0.5748   1.0000
   6.500   1.1999   0.03036   0.02279  -0.1250   0.5707   1.0000
   6.750   1.1948   0.03208   0.02465  -0.1208   0.5605   1.0000
   7.000   1.2471   0.03058   0.02310  -0.1231   0.5553   1.0000
   7.250   1.2538   0.03161   0.02424  -0.1201   0.5462   1.0000
   7.500   1.2968   0.03060   0.02321  -0.1214   0.5396   1.0000
   7.750   1.3131   0.03098   0.02366  -0.1195   0.5307   1.0000
   8.000   1.3559   0.02988   0.02254  -0.1206   0.5225   1.0000
   8.250   1.3656   0.03055   0.02332  -0.1179   0.5132   1.0000
   8.500   1.4062   0.02977   0.02253  -0.1190   0.5056   1.0000
   8.750   1.4126   0.03055   0.02345  -0.1158   0.4961   1.0000
   9.000   1.4587   0.02952   0.02236  -0.1176   0.4877   1.0000
   9.250   1.4557   0.03058   0.02361  -0.1132   0.4776   1.0000
   9.500   1.4870   0.03020   0.02326  -0.1131   0.4686   1.0000
   9.750   1.4972   0.03054   0.02371  -0.1102   0.4581   1.0000
  10.000   1.5032   0.03090   0.02417  -0.1067   0.4472   1.0000
  10.250   1.5196   0.03072   0.02400  -0.1044   0.4350   1.0000
  10.500   1.5316   0.03082   0.02414  -0.1016   0.4231   1.0000
  10.750   1.5233   0.03189   0.02537  -0.0968   0.4115   1.0000
  11.000   1.5245   0.03264   0.02620  -0.0933   0.3989   1.0000
  11.250   1.5254   0.03348   0.02710  -0.0899   0.3849   1.0000
  11.500   1.5216   0.03468   0.02836  -0.0865   0.3693   1.0000
  11.750   1.5144   0.03630   0.03003  -0.0831   0.3519   1.0000
  12.000   1.5065   0.03819   0.03194  -0.0801   0.3320   1.0000
  12.250   1.4983   0.04033   0.03399  -0.0774   0.3097   1.0000
  12.500   1.4847   0.04322   0.03683  -0.0748   0.2851   1.0000
  12.750   1.4724   0.04627   0.03971  -0.0727   0.2605   1.0000
  13.000   1.4601   0.04957   0.04282  -0.0708   0.2375   1.0000
  13.250   1.4498   0.05290   0.04595  -0.0693   0.2174   1.0000
  13.500   1.4409   0.05635   0.04928  -0.0681   0.1992   1.0000
  13.750   1.4347   0.05964   0.05245  -0.0670   0.1831   1.0000
  14.000   1.4322   0.06265   0.05533  -0.0661   0.1691   1.0000
  14.250   1.4341   0.06522   0.05775  -0.0652   0.1570   1.0000
  14.500   1.4410   0.06724   0.05955  -0.0643   0.1462   1.0000
  14.750   1.4411   0.07023   0.06266  -0.0639   0.1377   1.0000
  15.000   1.4486   0.07233   0.06466  -0.0632   0.1292   1.0000
  15.250   1.4540   0.07471   0.06704  -0.0628   0.1220   1.0000
  15.500   1.4640   0.07670   0.06904  -0.0621   0.1154   1.0000
  15.750   1.4681   0.07936   0.07180  -0.0619   0.1097   1.0000
  16.000   1.4812   0.08105   0.07343  -0.0613   0.1033   1.0000
  16.250   1.4759   0.08487   0.07753  -0.0616   0.0988   1.0000
  16.500   1.4890   0.08642   0.07888  -0.0611   0.0920   1.0000
  16.750   1.4747   0.09147   0.08431  -0.0621   0.0884   1.0000
  17.000   1.4702   0.09526   0.08822  -0.0628   0.0835   1.0000
  17.250   1.4697   0.09866   0.09167  -0.0633   0.0787   1.0000
  17.500   1.4627   0.10310   0.09631  -0.0644   0.0745   1.0000
  17.750   1.4701   0.10527   0.09832  -0.0645   0.0699   1.0000
  18.000   1.4607   0.11032   0.10368  -0.0660   0.0668   1.0000
  18.250   1.4632   0.11335   0.10671  -0.0667   0.0635   1.0000
  18.500   1.4712   0.11582   0.10919  -0.0667   0.0603   1.0000
  18.750   1.4602   0.12135   0.11503  -0.0687   0.0589   1.0000
  19.000   1.4502   0.12678   0.12072  -0.0709   0.0575   1.0000
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