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GOE 331 (PFALZ 60) AIRFOIL (goe331-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 331 (PFALZ 60) AIRFOIL (goe331-il)
Reynolds number: 100,000
Max Cl/Cd: 58.85 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe331-il-100000.txt
Download as CSV file: xf-goe331-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 331 (PFALZ 60) 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.2590   0.13089   0.12623  -0.0314   1.0000   0.0430
 -10.000  -0.2756   0.13145   0.12688  -0.0289   1.0000   0.0432
  -9.750  -0.2933   0.13214   0.12767  -0.0268   1.0000   0.0433
  -9.250  -0.2972   0.12690   0.12253  -0.0222   1.0000   0.0441
  -9.000  -0.3020   0.12520   0.12088  -0.0202   1.0000   0.0447
  -8.750  -0.2884   0.12184   0.11752  -0.0231   0.9967   0.0458
  -8.500  -0.2720   0.11839   0.11406  -0.0273   0.9922   0.0472
  -8.250  -0.2575   0.11529   0.11096  -0.0318   0.9866   0.0485
  -8.000  -0.2481   0.11327   0.10893  -0.0370   0.9800   0.0496
  -7.750  -0.2425   0.11224   0.10792  -0.0449   0.9712   0.0500
  -7.500  -0.2312   0.10817   0.10386  -0.0460   0.9646   0.0505
  -7.250  -0.2120   0.10349   0.09917  -0.0460   0.9609   0.0516
  -7.000  -0.1890   0.09970   0.09536  -0.0505   0.9566   0.0534
  -6.750  -0.1828   0.09740   0.09308  -0.0523   0.9472   0.0550
  -6.500  -0.1574   0.09488   0.09050  -0.0629   0.9394   0.0577
  -6.250  -0.1399   0.09297   0.08851  -0.0719   0.9288   0.0583
  -6.000  -0.1242   0.08779   0.08338  -0.0691   0.9266   0.0594
  -5.750  -0.1188   0.08541   0.08102  -0.0683   0.9184   0.0606
  -5.500  -0.0957   0.08219   0.07777  -0.0721   0.9127   0.0628
  -5.250  -0.0741   0.07955   0.07507  -0.0766   0.9058   0.0655
  -5.000  -0.0331   0.07767   0.07291  -0.0889   0.8972   0.0681
  -4.750  -0.0148   0.07283   0.06817  -0.0882   0.8946   0.0696
  -4.500  -0.0121   0.07108   0.06645  -0.0862   0.8849   0.0712
  -4.250   0.0541   0.06998   0.06482  -0.1003   0.8798   0.0791
  -3.750   0.0725   0.06299   0.05806  -0.0975   0.8667   0.0823
  -3.500   0.1412   0.06157   0.05609  -0.1086   0.8630   0.0920
  -3.250   0.1409   0.05849   0.05317  -0.1056   0.8528   0.0932
  -3.000   0.1783   0.05478   0.04948  -0.1089   0.8486   0.0987
  -2.750   0.2405   0.05101   0.04545  -0.1171   0.8461   0.1099
  -2.500   0.2515   0.05000   0.04439  -0.1153   0.8338   0.1167
  -2.250   0.3146   0.04703   0.04105  -0.1229   0.8311   0.1386
  -2.000   0.3273   0.04514   0.03925  -0.1213   0.8204   0.1464
  -1.750   0.3781   0.04213   0.03605  -0.1261   0.8164   0.1734
  -1.500   0.4272   0.03953   0.03326  -0.1303   0.8136   0.2203
  -1.250   0.4383   0.03802   0.03188  -0.1282   0.8022   0.2437
  -1.000   0.4728   0.03539   0.02930  -0.1295   0.7984   0.3121
  -0.750   0.4951   0.03377   0.02774  -0.1287   0.7908   0.3649
  -0.500   0.5236   0.03203   0.02599  -0.1286   0.7835   0.4129
  -0.250   0.5647   0.02978   0.02371  -0.1300   0.7797   0.4552
   0.000   0.5923   0.02922   0.02297  -0.1301   0.7689   0.4595
   0.250   0.6550   0.02834   0.02130  -0.1352   0.7637   0.3585
   0.500   0.6972   0.02857   0.02080  -0.1353   0.7542   0.2309
   0.750   0.7397   0.02771   0.01944  -0.1352   0.7473   0.1621
   1.000   0.7699   0.02726   0.01867  -0.1340   0.7379   0.1340
   1.250   0.8052   0.02625   0.01743  -0.1338   0.7301   0.1188
   1.500   0.8312   0.02554   0.01668  -0.1327   0.7195   0.1137
   1.750   0.8675   0.02442   0.01541  -0.1328   0.7118   0.1107
   2.000   0.8916   0.02408   0.01499  -0.1313   0.6991   0.1070
   2.250   0.9198   0.02337   0.01426  -0.1304   0.6879   0.1052
   2.500   0.9522   0.02239   0.01320  -0.1301   0.6780   0.1045
   2.750   0.9772   0.02196   0.01271  -0.1288   0.6635   0.1050
   3.000   1.0038   0.02150   0.01215  -0.1279   0.6484   0.1073
   3.250   1.0311   0.02104   0.01161  -0.1270   0.6319   0.1161
   3.500   1.0588   0.02065   0.01109  -0.1262   0.6140   0.1284
   3.750   1.0835   0.01897   0.01081  -0.1250   0.5952   1.0000
   4.000   1.1059   0.01913   0.01071  -0.1234   0.5726   1.0000
   4.250   1.1306   0.01933   0.01060  -0.1224   0.5517   1.0000
   4.500   1.1555   0.01964   0.01060  -0.1215   0.5325   1.0000
   4.750   1.1799   0.02005   0.01076  -0.1208   0.5150   1.0000
   5.000   1.2034   0.02054   0.01107  -0.1200   0.4991   1.0000
   5.250   1.2262   0.02108   0.01149  -0.1192   0.4849   1.0000
   5.500   1.2496   0.02166   0.01196  -0.1185   0.4730   1.0000
   5.750   1.2758   0.02221   0.01237  -0.1183   0.4634   1.0000
   6.000   1.2987   0.02283   0.01296  -0.1177   0.4537   1.0000
   6.250   1.3238   0.02345   0.01350  -0.1174   0.4457   1.0000
   6.500   1.3470   0.02408   0.01414  -0.1168   0.4375   1.0000
   6.750   1.3730   0.02474   0.01471  -0.1168   0.4307   1.0000
   7.000   1.3944   0.02547   0.01552  -0.1160   0.4238   1.0000
   7.250   1.4220   0.02613   0.01610  -0.1162   0.4182   1.0000
   7.500   1.4439   0.02697   0.01705  -0.1156   0.4127   1.0000
   7.750   1.4653   0.02776   0.01793  -0.1148   0.4068   1.0000
   8.000   1.4940   0.02846   0.01854  -0.1153   0.4017   1.0000
   8.250   1.5132   0.02944   0.01970  -0.1143   0.3968   1.0000
   8.500   1.5327   0.03038   0.02079  -0.1134   0.3918   1.0000
   8.750   1.5591   0.03114   0.02153  -0.1135   0.3868   1.0000
   9.000   1.5788   0.03212   0.02262  -0.1126   0.3812   1.0000
   9.250   1.5947   0.03304   0.02373  -0.1111   0.3750   1.0000
   9.500   1.6245   0.03372   0.02432  -0.1117   0.3693   1.0000
   9.750   1.6368   0.03495   0.02579  -0.1098   0.3643   1.0000
  10.000   1.6511   0.03608   0.02712  -0.1082   0.3592   1.0000
  10.250   1.6770   0.03693   0.02801  -0.1083   0.3543   1.0000
  10.500   1.6943   0.03823   0.02947  -0.1073   0.3497   1.0000
  10.750   1.7003   0.03971   0.03124  -0.1046   0.3450   1.0000
  11.000   1.7180   0.04085   0.03252  -0.1036   0.3402   1.0000
  11.250   1.7531   0.04186   0.03349  -0.1052   0.3355   1.0000
  11.500   1.7411   0.04387   0.03593  -0.1001   0.3310   1.0000
  11.750   1.7484   0.04519   0.03744  -0.0978   0.3253   1.0000
  12.000   1.7797   0.04552   0.03772  -0.0984   0.3175   1.0000
  12.250   1.7640   0.04736   0.03988  -0.0930   0.3117   1.0000
  12.500   1.7967   0.04654   0.03891  -0.0934   0.3005   1.0000
  12.750   1.7765   0.04823   0.04087  -0.0873   0.2949   1.0000
  13.000   1.8047   0.04731   0.03980  -0.0871   0.2843   1.0000
  13.250   1.7785   0.04943   0.04223  -0.0809   0.2796   1.0000
  13.500   1.8111   0.04817   0.04079  -0.0810   0.2695   1.0000
  13.750   1.7775   0.05103   0.04401  -0.0749   0.2656   1.0000
  14.000   1.7654   0.05274   0.04589  -0.0714   0.2596   1.0000
  14.250   1.7756   0.05291   0.04607  -0.0697   0.2522   1.0000
  14.500   1.7467   0.05652   0.04998  -0.0660   0.2476   1.0000
  14.750   1.7691   0.05542   0.04879  -0.0651   0.2389   1.0000
  15.000   1.7323   0.06037   0.05411  -0.0620   0.2350   1.0000
  15.250   1.7125   0.06389   0.05784  -0.0602   0.2292   1.0000
  15.500   1.7106   0.06547   0.05950  -0.0590   0.2218   1.0000
  15.750   1.6767   0.07144   0.06575  -0.0581   0.2171   1.0000
  16.000   1.6763   0.07311   0.06745  -0.0576   0.2082   1.0000
  16.250   1.6368   0.08092   0.07555  -0.0580   0.2039   1.0000
  16.500   1.6295   0.08415   0.07885  -0.0584   0.1941   1.0000
  16.750   1.5844   0.09401   0.08896  -0.0606   0.1909   1.0000
  17.000   1.5723   0.09871   0.09372  -0.0620   0.1803   1.0000
  17.250   1.5189   0.11109   0.10628  -0.0660   0.1789   1.0000
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