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GOE 332 (PFALZ 61) AIRFOIL (goe332-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 332 (PFALZ 61) AIRFOIL (goe332-il)
Reynolds number: 500,000
Max Cl/Cd: 120.72 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe332-il-500000.txt
Download as CSV file: xf-goe332-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 332 (PFALZ 61) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.0555   0.07392   0.07138  -0.1030   0.8922   0.0320
  -7.750  -0.0437   0.07128   0.06862  -0.1025   0.8724   0.0323
  -7.500  -0.0306   0.06914   0.06637  -0.1029   0.8552   0.0326
  -7.250  -0.0171   0.06691   0.06407  -0.1042   0.8406   0.0330
  -7.000  -0.0028   0.06444   0.06153  -0.1064   0.8277   0.0335
  -6.750   0.0129   0.06166   0.05867  -0.1097   0.8162   0.0342
  -6.500   0.0307   0.05843   0.05534  -0.1141   0.8056   0.0354
  -6.250   0.0600   0.04911   0.04580  -0.1299   0.7953   0.0380
  -6.000   0.0771   0.04729   0.04391  -0.1303   0.7866   0.0384
  -5.750   0.0966   0.04543   0.04199  -0.1312   0.7773   0.0389
  -5.500   0.1181   0.04336   0.03982  -0.1328   0.7691   0.0396
  -5.250   0.1416   0.04079   0.03715  -0.1351   0.7605   0.0409
  -5.000   0.1735   0.03302   0.02887  -0.1420   0.7538   0.0451
  -4.750   0.1957   0.03171   0.02753  -0.1422   0.7454   0.0456
  -4.250   0.2438   0.02917   0.02480  -0.1431   0.7305   0.0481
  -4.000   0.2716   0.02481   0.01992  -0.1448   0.7240   0.0536
  -3.750   0.2965   0.02389   0.01895  -0.1450   0.7170   0.0546
  -3.500   0.3222   0.02294   0.01791  -0.1451   0.7100   0.0562
  -3.250   0.3513   0.01633   0.01012  -0.1453   0.7050   0.0431
  -3.000   0.3784   0.01504   0.00862  -0.1452   0.6982   0.0426
  -2.750   0.4058   0.01405   0.00740  -0.1450   0.6917   0.0422
  -2.500   0.4333   0.01327   0.00644  -0.1449   0.6852   0.0419
  -2.250   0.4608   0.01270   0.00573  -0.1447   0.6783   0.0420
  -2.000   0.4883   0.01228   0.00518  -0.1446   0.6722   0.0423
  -1.750   0.5159   0.01189   0.00475  -0.1444   0.6659   0.0428
  -1.500   0.5435   0.01160   0.00438  -0.1443   0.6602   0.0433
  -1.250   0.5712   0.01140   0.00412  -0.1442   0.6548   0.0440
  -1.000   0.5986   0.01101   0.00372  -0.1441   0.6491   0.0453
  -0.750   0.6261   0.01076   0.00345  -0.1440   0.6436   0.0468
  -0.500   0.6538   0.01062   0.00329  -0.1440   0.6386   0.0483
  -0.250   0.6815   0.01048   0.00316  -0.1439   0.6331   0.0502
   0.000   0.7092   0.01042   0.00305  -0.1438   0.6276   0.0522
   0.250   0.7370   0.01031   0.00293  -0.1438   0.6224   0.0572
   0.750   0.7922   0.01008   0.00296  -0.1437   0.6115   0.1449
   1.000   0.8197   0.01010   0.00299  -0.1437   0.6062   0.1670
   1.250   0.8471   0.01005   0.00302  -0.1436   0.6002   0.1907
   1.500   0.8738   0.00960   0.00314  -0.1439   0.5945   0.4268
   1.750   0.8960   0.00853   0.00328  -0.1425   0.5894   1.0000
   2.000   0.9231   0.00860   0.00332  -0.1423   0.5833   1.0000
   2.250   0.9499   0.00872   0.00336  -0.1421   0.5772   1.0000
   2.500   0.9767   0.00882   0.00342  -0.1419   0.5708   1.0000
   2.750   1.0033   0.00892   0.00348  -0.1416   0.5638   1.0000
   3.000   1.0298   0.00906   0.00355  -0.1414   0.5575   1.0000
   3.250   1.0564   0.00914   0.00364  -0.1412   0.5502   1.0000
   3.500   1.0823   0.00930   0.00372  -0.1408   0.5431   1.0000
   3.750   1.1085   0.00939   0.00382  -0.1405   0.5349   1.0000
   4.250   1.1595   0.00967   0.00403  -0.1397   0.5166   1.0000
   4.500   1.1843   0.00983   0.00415  -0.1392   0.5056   1.0000
   4.750   1.2083   0.01002   0.00428  -0.1385   0.4936   1.0000
   5.000   1.2325   0.01021   0.00444  -0.1378   0.4813   1.0000
   5.250   1.2567   0.01042   0.00462  -0.1372   0.4695   1.0000
   5.500   1.2802   0.01065   0.00481  -0.1365   0.4580   1.0000
   5.750   1.3030   0.01093   0.00502  -0.1357   0.4467   1.0000
   6.000   1.3263   0.01118   0.00526  -0.1349   0.4351   1.0000
   6.250   1.3493   0.01144   0.00550  -0.1342   0.4245   1.0000
   6.500   1.3712   0.01176   0.00577  -0.1332   0.4145   1.0000
   6.750   1.3937   0.01203   0.00604  -0.1323   0.4045   1.0000
   7.000   1.4155   0.01234   0.00633  -0.1314   0.3945   1.0000
   7.250   1.4354   0.01271   0.00665  -0.1301   0.3833   1.0000
   7.500   1.4558   0.01304   0.00697  -0.1289   0.3718   1.0000
   7.750   1.4758   0.01338   0.00731  -0.1276   0.3611   1.0000
   8.000   1.4929   0.01377   0.00766  -0.1258   0.3508   1.0000
   8.250   1.5106   0.01415   0.00803  -0.1241   0.3406   1.0000
   8.500   1.5286   0.01453   0.00842  -0.1225   0.3311   1.0000
   8.750   1.5442   0.01502   0.00888  -0.1206   0.3213   1.0000
   9.000   1.5621   0.01542   0.00931  -0.1190   0.3111   1.0000
   9.250   1.5783   0.01590   0.00979  -0.1173   0.3011   1.0000
   9.500   1.5921   0.01650   0.01036  -0.1152   0.2888   1.0000
   9.750   1.6052   0.01715   0.01098  -0.1131   0.2749   1.0000
  10.250   1.6288   0.01866   0.01243  -0.1087   0.2433   1.0000
  10.500   1.6362   0.01971   0.01340  -0.1060   0.2215   1.0000
  10.750   1.6387   0.02112   0.01468  -0.1029   0.1968   1.0000
  11.000   1.6372   0.02288   0.01630  -0.0996   0.1721   1.0000
  11.250   1.6343   0.02488   0.01817  -0.0965   0.1476   1.0000
  11.500   1.6272   0.02735   0.02047  -0.0932   0.1163   1.0000
  11.750   1.6128   0.03058   0.02348  -0.0898   0.0853   1.0000
  12.250   1.5841   0.03763   0.03025  -0.0842   0.0351   1.0000
  12.500   1.5790   0.04056   0.03321  -0.0825   0.0296   1.0000
  12.750   1.5759   0.04340   0.03611  -0.0810   0.0269   1.0000
  13.000   1.5773   0.04585   0.03866  -0.0799   0.0254   1.0000
  13.250   1.5762   0.04863   0.04154  -0.0789   0.0242   1.0000
  13.500   1.5721   0.05183   0.04482  -0.0778   0.0232   1.0000
  13.750   1.5661   0.05534   0.04843  -0.0770   0.0223   1.0000
  14.000   1.5656   0.05827   0.05147  -0.0763   0.0218   1.0000
  14.250   1.5634   0.06148   0.05478  -0.0758   0.0212   1.0000
  14.500   1.5602   0.06488   0.05829  -0.0754   0.0207   1.0000
  14.750   1.5554   0.06855   0.06205  -0.0751   0.0202   1.0000
  15.000   1.5492   0.07243   0.06604  -0.0749   0.0197   1.0000
  15.250   1.5410   0.07667   0.07037  -0.0748   0.0193   1.0000
  15.500   1.5299   0.08141   0.07521  -0.0749   0.0189   1.0000
  15.750   1.5158   0.08663   0.08054  -0.0752   0.0185   1.0000
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