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GOE 332 (PFALZ 61) AIRFOIL (goe332-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 332 (PFALZ 61) AIRFOIL (goe332-il)
Reynolds number: 200,000
Max Cl/Cd: 83.56 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe332-il-200000.txt
Download as CSV file: xf-goe332-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.1384   0.09674   0.09333  -0.0673   0.9731   0.0496
  -8.250  -0.1271   0.09335   0.08994  -0.0785   0.9609   0.0519
  -8.000  -0.1128   0.08835   0.08494  -0.0891   0.9482   0.0525
  -7.750  -0.0886   0.08415   0.08072  -0.0864   0.9474   0.0533
  -7.500  -0.0680   0.08089   0.07745  -0.0877   0.9389   0.0544
  -7.250  -0.0438   0.07732   0.07385  -0.0921   0.9327   0.0564
  -7.000  -0.0233   0.07371   0.07020  -0.0984   0.9208   0.0594
  -6.750   0.0056   0.06738   0.06373  -0.1171   0.9062   0.0622
  -6.500   0.0240   0.06450   0.06084  -0.1154   0.8985   0.0631
  -6.250   0.0449   0.06188   0.05817  -0.1162   0.8890   0.0645
  -6.000   0.0653   0.05918   0.05540  -0.1189   0.8774   0.0667
  -5.750   0.1034   0.05358   0.04940  -0.1345   0.8647   0.0729
  -5.500   0.1192   0.05103   0.04685  -0.1331   0.8560   0.0739
  -5.250   0.1356   0.04933   0.04514  -0.1321   0.8456   0.0756
  -5.000   0.1759   0.04630   0.04153  -0.1414   0.8365   0.0848
  -4.750   0.1907   0.04316   0.03850  -0.1405   0.8271   0.0859
  -4.500   0.2108   0.04129   0.03660  -0.1403   0.8195   0.0875
  -4.250   0.2474   0.04107   0.03578  -0.1440   0.8102   0.0977
  -4.000   0.2657   0.03673   0.03152  -0.1446   0.8037   0.0995
  -3.750   0.2857   0.03500   0.02982  -0.1442   0.7952   0.1014
  -3.500   0.3175   0.03428   0.02875  -0.1456   0.7888   0.1113
  -3.250   0.3390   0.03152   0.02591  -0.1461   0.7810   0.1152
  -3.000   0.3634   0.03010   0.02445  -0.1462   0.7743   0.1191
  -2.750   0.4043   0.02289   0.01577  -0.1480   0.7693   0.0729
  -2.500   0.4299   0.02120   0.01396  -0.1479   0.7619   0.0700
  -2.250   0.4590   0.01950   0.01189  -0.1480   0.7563   0.0675
  -2.000   0.4858   0.01845   0.01059  -0.1476   0.7494   0.0673
  -1.750   0.5136   0.01773   0.00967  -0.1474   0.7427   0.0687
  -1.500   0.5424   0.01701   0.00874  -0.1473   0.7371   0.0692
  -1.250   0.5684   0.01644   0.00809  -0.1468   0.7294   0.0700
  -1.000   0.5969   0.01595   0.00748  -0.1466   0.7235   0.0715
  -0.750   0.6230   0.01550   0.00702  -0.1462   0.7166   0.0735
  -0.500   0.6501   0.01518   0.00673  -0.1459   0.7100   0.0779
  -0.250   0.6788   0.01501   0.00649  -0.1459   0.7046   0.0846
   0.000   0.7043   0.01479   0.00637  -0.1454   0.6974   0.0948
   0.250   0.7327   0.01450   0.00620  -0.1454   0.6915   0.1338
   0.500   0.7592   0.01430   0.00616  -0.1452   0.6852   0.2013
   0.750   0.7855   0.01403   0.00615  -0.1451   0.6784   0.2775
   1.000   0.8118   0.01256   0.00615  -0.1443   0.6733   1.0000
   1.250   0.8367   0.01272   0.00623  -0.1436   0.6659   1.0000
   1.500   0.8644   0.01283   0.00619  -0.1435   0.6595   1.0000
   1.750   0.8909   0.01300   0.00625  -0.1432   0.6529   1.0000
   2.000   0.9172   0.01314   0.00631  -0.1428   0.6457   1.0000
   2.250   0.9458   0.01330   0.00632  -0.1429   0.6399   1.0000
   2.500   0.9699   0.01346   0.00648  -0.1421   0.6316   1.0000
   2.750   0.9980   0.01359   0.00649  -0.1421   0.6251   1.0000
   3.000   1.0225   0.01378   0.00668  -0.1415   0.6171   1.0000
   3.250   1.0496   0.01392   0.00674  -0.1413   0.6101   1.0000
   3.500   1.0747   0.01412   0.00692  -0.1407   0.6023   1.0000
   3.750   1.1009   0.01426   0.00701  -0.1404   0.5944   1.0000
   4.000   1.1259   0.01445   0.00718  -0.1398   0.5862   1.0000
   4.250   1.1516   0.01460   0.00730  -0.1394   0.5781   1.0000
   4.500   1.1763   0.01480   0.00750  -0.1388   0.5698   1.0000
   4.750   1.2017   0.01495   0.00761  -0.1384   0.5612   1.0000
   5.000   1.2254   0.01515   0.00783  -0.1376   0.5519   1.0000
   5.250   1.2511   0.01532   0.00794  -0.1372   0.5437   1.0000
   5.500   1.2735   0.01553   0.00820  -0.1362   0.5335   1.0000
   5.750   1.2977   0.01571   0.00833  -0.1355   0.5239   1.0000
   6.000   1.3200   0.01587   0.00849  -0.1345   0.5129   1.0000
   6.250   1.3413   0.01608   0.00873  -0.1333   0.5013   1.0000
   6.500   1.3640   0.01633   0.00894  -0.1324   0.4911   1.0000
   6.750   1.3862   0.01659   0.00918  -0.1314   0.4811   1.0000
   7.000   1.4072   0.01690   0.00954  -0.1303   0.4706   1.0000
   7.250   1.4297   0.01724   0.00983  -0.1294   0.4615   1.0000
   7.500   1.4501   0.01758   0.01022  -0.1282   0.4516   1.0000
   7.750   1.4713   0.01797   0.01063  -0.1271   0.4426   1.0000
   8.000   1.4922   0.01836   0.01100  -0.1261   0.4337   1.0000
   8.250   1.5110   0.01876   0.01148  -0.1246   0.4241   1.0000
   8.500   1.5305   0.01919   0.01186  -0.1233   0.4144   1.0000
   8.750   1.5455   0.01959   0.01232  -0.1211   0.4030   1.0000
   9.000   1.5591   0.02004   0.01280  -0.1188   0.3912   1.0000
   9.250   1.5715   0.02051   0.01328  -0.1162   0.3801   1.0000
   9.500   1.5831   0.02103   0.01378  -0.1136   0.3698   1.0000
   9.750   1.5933   0.02158   0.01442  -0.1108   0.3593   1.0000
  10.000   1.6037   0.02220   0.01508  -0.1081   0.3491   1.0000
  10.250   1.6122   0.02291   0.01579  -0.1053   0.3382   1.0000
  10.500   1.6201   0.02366   0.01664  -0.1025   0.3268   1.0000
  10.750   1.6284   0.02450   0.01753  -0.0999   0.3165   1.0000
  11.000   1.6346   0.02549   0.01851  -0.0972   0.3061   1.0000
  11.250   1.6407   0.02652   0.01967  -0.0947   0.2941   1.0000
  11.500   1.6446   0.02777   0.02098  -0.0922   0.2807   1.0000
  11.750   1.6475   0.02920   0.02246  -0.0897   0.2668   1.0000
  12.000   1.6495   0.03082   0.02412  -0.0874   0.2521   1.0000
  12.250   1.6490   0.03274   0.02605  -0.0852   0.2355   1.0000
  12.500   1.6435   0.03520   0.02847  -0.0829   0.2157   1.0000
  12.750   1.6361   0.03798   0.03119  -0.0807   0.1932   1.0000
  13.000   1.6238   0.04136   0.03448  -0.0785   0.1717   1.0000
  13.250   1.6086   0.04523   0.03823  -0.0766   0.1474   1.0000
  13.500   1.5919   0.04948   0.04235  -0.0749   0.1187   1.0000
  13.750   1.5712   0.05436   0.04706  -0.0735   0.0927   1.0000
  14.000   1.5521   0.05928   0.05189  -0.0724   0.0756   1.0000
  14.250   1.5370   0.06396   0.05654  -0.0716   0.0589   1.0000
  14.500   1.5232   0.06861   0.06116  -0.0712   0.0491   1.0000
  14.750   1.5110   0.07324   0.06580  -0.0709   0.0445   1.0000
  15.000   1.5007   0.07776   0.07041  -0.0709   0.0419   1.0000
  15.250   1.4894   0.08253   0.07526  -0.0710   0.0401   1.0000
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