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GOE 79 (PFALZ 11) AIRFOIL (goe79-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 79 (PFALZ 11) AIRFOIL (goe79-il)
Reynolds number: 100,000
Max Cl/Cd: 57.55 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe79-il-100000.txt
Download as CSV file: xf-goe79-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 79 (PFALZ 11) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3293   0.11441   0.10925  -0.0097   1.0000   0.0389
  -8.750  -0.3261   0.11338   0.10828  -0.0124   1.0000   0.0392
  -8.500  -0.3226   0.11143   0.10640  -0.0143   1.0000   0.0394
  -8.250  -0.3089   0.10577   0.10075  -0.0129   1.0000   0.0402
  -8.000  -0.3014   0.10275   0.09777  -0.0133   1.0000   0.0409
  -7.750  -0.2951   0.10015   0.09521  -0.0140   1.0000   0.0417
  -7.500  -0.2891   0.09769   0.09281  -0.0149   1.0000   0.0425
  -7.250  -0.2810   0.09518   0.09036  -0.0165   1.0000   0.0434
  -7.000  -0.2718   0.09286   0.08809  -0.0188   1.0000   0.0443
  -6.750  -0.2601   0.09128   0.08656  -0.0233   1.0000   0.0450
  -6.250  -0.2400   0.08610   0.08150  -0.0276   1.0000   0.0458
  -6.000  -0.2360   0.08284   0.07831  -0.0255   1.0000   0.0465
  -5.750  -0.2318   0.08048   0.07604  -0.0249   1.0000   0.0474
  -5.500  -0.2294   0.07864   0.07427  -0.0243   1.0000   0.0484
  -5.250  -0.2282   0.07708   0.07277  -0.0239   1.0000   0.0495
  -5.000  -0.2258   0.07568   0.07142  -0.0242   1.0000   0.0506
  -4.750  -0.2175   0.07464   0.07039  -0.0265   1.0000   0.0518
  -4.500  -0.1660   0.07102   0.06664  -0.0383   0.9941   0.0531
  -4.250  -0.1361   0.06627   0.06191  -0.0418   0.9865   0.0547
  -4.000  -0.0900   0.06247   0.05804  -0.0497   0.9781   0.0578
  -3.750  -0.0147   0.05939   0.05467  -0.0648   0.9709   0.0619
  -3.500   0.0127   0.05502   0.05036  -0.0673   0.9612   0.0645
  -3.250   0.0916   0.05392   0.04881  -0.0808   0.9525   0.0719
  -3.000   0.1193   0.04841   0.04347  -0.0836   0.9456   0.0741
  -2.750   0.1675   0.04548   0.04044  -0.0897   0.9368   0.0804
  -2.500   0.2234   0.04227   0.03705  -0.0971   0.9289   0.0860
  -2.000   0.3099   0.03715   0.03167  -0.1052   0.9023   0.1009
  -1.750   0.3489   0.03520   0.02953  -0.1080   0.8873   0.1122
  -1.500   0.3828   0.03356   0.02771  -0.1095   0.8723   0.1251
  -1.250   0.4133   0.03200   0.02602  -0.1104   0.8578   0.1398
  -1.000   0.4406   0.03040   0.02433  -0.1107   0.8437   0.1575
  -0.750   0.4680   0.02926   0.02305  -0.1109   0.8285   0.1873
  -0.500   0.4918   0.02768   0.02146  -0.1107   0.8133   0.2216
   0.000   0.5384   0.02482   0.01856  -0.1096   0.7843   0.3458
   0.250   0.5628   0.02323   0.01698  -0.1088   0.7704   0.3967
   0.500   0.5878   0.02169   0.01545  -0.1078   0.7569   0.4435
   0.750   0.6168   0.02054   0.01420  -0.1074   0.7429   0.4714
   1.000   0.6528   0.02035   0.01367  -0.1082   0.7271   0.4463
   1.250   0.6916   0.02049   0.01331  -0.1088   0.7111   0.3571
   1.500   0.7289   0.02100   0.01322  -0.1080   0.6950   0.2421
   1.750   0.7610   0.02081   0.01262  -0.1067   0.6787   0.1771
   2.000   0.7903   0.02044   0.01194  -0.1054   0.6616   0.1447
   2.250   0.8182   0.02009   0.01134  -0.1041   0.6436   0.1283
   2.500   0.8453   0.02000   0.01097  -0.1028   0.6244   0.1214
   2.750   0.8715   0.01958   0.01052  -0.1019   0.6022   0.1168
   3.000   0.8977   0.01945   0.01021  -0.1007   0.5801   0.1110
   3.250   0.9236   0.01940   0.00996  -0.0995   0.5586   0.1085
   3.500   0.9489   0.01928   0.00974  -0.0985   0.5354   0.1079
   3.750   0.9746   0.01927   0.00959  -0.0976   0.5131   0.1094
   4.000   1.0006   0.01928   0.00947  -0.0969   0.4930   0.1166
   4.250   1.0268   0.01945   0.00945  -0.0962   0.4747   0.1230
   4.750   1.0757   0.01869   0.00980  -0.0944   0.4430   1.0000
   5.000   1.1015   0.01915   0.01004  -0.0937   0.4289   1.0000
   5.250   1.1271   0.01962   0.01037  -0.0931   0.4161   1.0000
   5.500   1.1526   0.02013   0.01072  -0.0926   0.4049   1.0000
   5.750   1.1782   0.02064   0.01112  -0.0921   0.3943   1.0000
   6.000   1.2034   0.02121   0.01170  -0.0916   0.3839   1.0000
   6.250   1.2290   0.02181   0.01218  -0.0912   0.3754   1.0000
   6.500   1.2538   0.02240   0.01284  -0.0907   0.3659   1.0000
   6.750   1.2786   0.02302   0.01345  -0.0902   0.3566   1.0000
   7.000   1.3033   0.02361   0.01405  -0.0897   0.3475   1.0000
   7.250   1.3275   0.02430   0.01481  -0.0892   0.3389   1.0000
   7.500   1.3520   0.02487   0.01531  -0.0886   0.3287   1.0000
   7.750   1.3742   0.02545   0.01607  -0.0878   0.3176   1.0000
   8.000   1.3974   0.02609   0.01675  -0.0871   0.3076   1.0000
   8.250   1.4203   0.02666   0.01732  -0.0864   0.2964   1.0000
   8.500   1.4406   0.02720   0.01807  -0.0853   0.2830   1.0000
   8.750   1.4601   0.02770   0.01867  -0.0840   0.2676   1.0000
   9.000   1.4781   0.02817   0.01920  -0.0825   0.2497   1.0000
   9.250   1.4940   0.02882   0.01984  -0.0808   0.2294   1.0000
   9.500   1.5078   0.02969   0.02084  -0.0788   0.2077   1.0000
   9.750   1.5224   0.03071   0.02184  -0.0770   0.1909   1.0000
  10.000   1.5373   0.03188   0.02302  -0.0753   0.1779   1.0000
  10.250   1.5521   0.03307   0.02420  -0.0737   0.1677   1.0000
  10.500   1.5664   0.03424   0.02537  -0.0720   0.1587   1.0000
  10.750   1.5796   0.03564   0.02694  -0.0702   0.1506   1.0000
  11.000   1.5931   0.03696   0.02813  -0.0686   0.1433   1.0000
  11.250   1.6022   0.03843   0.02987  -0.0664   0.1361   1.0000
  11.500   1.6130   0.03992   0.03127  -0.0647   0.1295   1.0000
  11.750   1.6172   0.04156   0.03315  -0.0621   0.1233   1.0000
  12.000   1.6270   0.04326   0.03472  -0.0603   0.1171   1.0000
  12.250   1.6248   0.04523   0.03700  -0.0572   0.1123   1.0000
  12.500   1.6369   0.04712   0.03871  -0.0559   0.1059   1.0000
  12.750   1.6330   0.04970   0.04160  -0.0532   0.1018   1.0000
  13.000   1.6332   0.05212   0.04415  -0.0513   0.0970   1.0000
  13.250   1.6439   0.05515   0.04714  -0.0502   0.0913   1.0000
  13.500   1.6325   0.05833   0.05068  -0.0480   0.0883   1.0000
  13.750   1.6269   0.06152   0.05405  -0.0466   0.0847   1.0000
  14.000   1.6394   0.06543   0.05789  -0.0457   0.0796   1.0000
  14.250   1.6184   0.06946   0.06228  -0.0445   0.0785   1.0000
  14.500   1.5974   0.07411   0.06727  -0.0442   0.0773   1.0000
  14.750   1.5757   0.07933   0.07279  -0.0446   0.0762   1.0000
  15.000   1.5528   0.08514   0.07889  -0.0459   0.0754   1.0000
  15.250   1.5269   0.09175   0.08577  -0.0481   0.0749   1.0000
  15.500   1.4955   0.09970   0.09401  -0.0516   0.0751   1.0000
  15.750   1.4565   0.10964   0.10424  -0.0570   0.0762   1.0000
  16.000   1.4132   0.12167   0.11651  -0.0644   0.0778   1.0000
  16.250   1.3677   0.13583   0.13084  -0.0734   0.0794   1.0000
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