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GOE 329 (PFALZ 58) AIRFOIL (goe329-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 329 (PFALZ 58) AIRFOIL (goe329-il)
Reynolds number: 500,000
Max Cl/Cd: 104.53 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe329-il-500000.txt
Download as CSV file: xf-goe329-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 329 (PFALZ 58) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2664   0.10969   0.10744  -0.0346   1.0000   0.0190
  -9.500  -0.2610   0.10689   0.10466  -0.0356   1.0000   0.0195
  -9.250  -0.2576   0.10427   0.10208  -0.0362   1.0000   0.0200
  -9.000  -0.2513   0.10135   0.09918  -0.0380   0.9977   0.0206
  -8.750  -0.1308   0.08083   0.07867  -0.0596   0.9405   0.0214
  -8.500  -0.1226   0.07769   0.07551  -0.0589   0.9288   0.0215
  -8.250  -0.1168   0.07477   0.07255  -0.0588   0.9176   0.0217
  -8.000  -0.1984   0.08467   0.08244  -0.0593   0.9440   0.0214
  -7.750  -0.1888   0.08185   0.07959  -0.0589   0.9314   0.0216
  -7.500  -0.1799   0.07914   0.07684  -0.0598   0.9191   0.0217
  -7.250  -0.1692   0.07629   0.07394  -0.0619   0.9081   0.0220
  -7.000  -0.1567   0.07331   0.07091  -0.0647   0.8976   0.0223
  -6.750  -0.1420   0.07017   0.06773  -0.0682   0.8879   0.0228
  -6.500  -0.1254   0.06692   0.06440  -0.0720   0.8794   0.0234
  -6.250  -0.1048   0.06327   0.06070  -0.0771   0.8705   0.0244
  -6.000  -0.0647   0.05754   0.05471  -0.0897   0.8626   0.0253
  -5.750  -0.0370   0.05327   0.05027  -0.0947   0.8547   0.0254
  -5.500  -0.0234   0.04963   0.04659  -0.0953   0.8480   0.0256
  -5.250  -0.0048   0.04714   0.04407  -0.0962   0.8404   0.0258
  -5.000   0.0161   0.04483   0.04169  -0.0974   0.8333   0.0262
  -4.750   0.0398   0.04245   0.03923  -0.0991   0.8258   0.0267
  -4.500   0.0659   0.03989   0.03653  -0.1010   0.8185   0.0275
  -4.250   0.0943   0.03714   0.03363  -0.1031   0.8113   0.0286
  -4.000   0.1371   0.03375   0.02968  -0.1058   0.8042   0.0303
  -3.750   0.1597   0.03010   0.02594  -0.1071   0.7969   0.0307
  -3.500   0.1844   0.02834   0.02412  -0.1079   0.7882   0.0311
  -3.250   0.2105   0.02678   0.02244  -0.1086   0.7798   0.0317
  -3.000   0.2379   0.02527   0.02079  -0.1092   0.7709   0.0327
  -2.750   0.2673   0.02365   0.01898  -0.1097   0.7617   0.0345
  -2.500   0.3002   0.02154   0.01631  -0.1100   0.7525   0.0368
  -2.250   0.3269   0.02001   0.01475  -0.1106   0.7408   0.0376
  -2.000   0.3545   0.01898   0.01363  -0.1111   0.7286   0.0388
  -1.750   0.3833   0.01808   0.01255  -0.1113   0.7157   0.0412
  -1.500   0.4132   0.01693   0.01103  -0.1114   0.7015   0.0451
  -1.250   0.4407   0.01608   0.01011  -0.1117   0.6844   0.0468
  -1.000   0.4689   0.01570   0.00954  -0.1117   0.6647   0.0507
  -0.750   0.4969   0.01485   0.00846  -0.1119   0.6435   0.0560
  -0.500   0.5244   0.01463   0.00810  -0.1119   0.6199   0.0614
   0.000   0.5794   0.01370   0.00677  -0.1121   0.5734   0.0798
   0.250   0.6063   0.01349   0.00646  -0.1121   0.5516   0.0881
   0.750   0.6644   0.01207   0.00455  -0.1110   0.5164   0.0498
   1.000   0.6923   0.01193   0.00422  -0.1107   0.5016   0.0441
   1.250   0.7197   0.01172   0.00395  -0.1107   0.4884   0.0433
   1.500   0.7474   0.01159   0.00376  -0.1107   0.4764   0.0440
   1.750   0.7751   0.01144   0.00359  -0.1107   0.4657   0.0435
   2.000   0.8028   0.01135   0.00345  -0.1108   0.4558   0.0432
   2.250   0.8306   0.01131   0.00337  -0.1109   0.4463   0.0433
   2.500   0.8583   0.01132   0.00335  -0.1110   0.4381   0.0439
   2.750   0.8860   0.01134   0.00332  -0.1110   0.4303   0.0458
   3.000   0.9135   0.01143   0.00338  -0.1110   0.4233   0.0487
   3.250   0.9410   0.01152   0.00346  -0.1111   0.4164   0.0559
   3.500   0.9595   0.00994   0.00376  -0.1095   0.4107   1.0000
   3.750   0.9872   0.01008   0.00386  -0.1096   0.4044   1.0000
   4.000   1.0141   0.01030   0.00400  -0.1095   0.3984   1.0000
   4.250   1.0411   0.01050   0.00417  -0.1095   0.3932   1.0000
   4.500   1.0684   0.01067   0.00433  -0.1095   0.3879   1.0000
   4.750   1.0950   0.01090   0.00452  -0.1095   0.3829   1.0000
   5.000   1.1216   0.01114   0.00473  -0.1094   0.3782   1.0000
   5.250   1.1487   0.01130   0.00492  -0.1094   0.3734   1.0000
   5.500   1.1751   0.01153   0.00513  -0.1093   0.3688   1.0000
   5.750   1.2010   0.01180   0.00537  -0.1092   0.3636   1.0000
   6.000   1.2278   0.01193   0.00555  -0.1091   0.3572   1.0000
   6.250   1.2530   0.01220   0.00577  -0.1089   0.3502   1.0000
   6.500   1.2795   0.01233   0.00596  -0.1088   0.3430   1.0000
   6.750   1.3046   0.01259   0.00619  -0.1085   0.3356   1.0000
   7.000   1.3306   0.01276   0.00641  -0.1084   0.3284   1.0000
   7.250   1.3552   0.01302   0.00665  -0.1081   0.3205   1.0000
   7.500   1.3808   0.01321   0.00690  -0.1079   0.3135   1.0000
   7.750   1.4048   0.01350   0.00717  -0.1074   0.3031   1.0000
   8.000   1.4288   0.01377   0.00744  -0.1070   0.2903   1.0000
   8.250   1.4519   0.01411   0.00774  -0.1065   0.2694   1.0000
   8.500   1.4668   0.01509   0.00838  -0.1047   0.2109   1.0000
   8.750   1.4506   0.01853   0.01084  -0.0986   0.0688   1.0000
   9.000   1.4519   0.02026   0.01232  -0.0948   0.0309   1.0000
   9.250   1.4625   0.02110   0.01322  -0.0921   0.0270   1.0000
   9.500   1.4717   0.02208   0.01424  -0.0895   0.0246   1.0000
   9.750   1.4796   0.02320   0.01545  -0.0868   0.0229   1.0000
  10.000   1.4898   0.02421   0.01654  -0.0847   0.0219   1.0000
  10.250   1.4982   0.02540   0.01783  -0.0826   0.0210   1.0000
  10.500   1.5047   0.02679   0.01931  -0.0804   0.0202   1.0000
  10.750   1.5078   0.02852   0.02113  -0.0782   0.0195   1.0000
  11.000   1.5054   0.03081   0.02353  -0.0758   0.0189   1.0000
  11.250   1.5008   0.03345   0.02630  -0.0736   0.0184   1.0000
  11.500   1.5052   0.03542   0.02837  -0.0722   0.0181   1.0000
  11.750   1.5070   0.03771   0.03077  -0.0710   0.0176   1.0000
  12.000   1.5073   0.04026   0.03343  -0.0699   0.0172   1.0000
  12.250   1.5056   0.04312   0.03639  -0.0689   0.0168   1.0000
  12.500   1.5025   0.04626   0.03964  -0.0682   0.0164   1.0000
  12.750   1.4980   0.04968   0.04316  -0.0676   0.0161   1.0000
  13.000   1.4924   0.05335   0.04694  -0.0673   0.0159   1.0000
  13.250   1.4862   0.05725   0.05093  -0.0671   0.0157   1.0000
  13.500   1.4791   0.06135   0.05512  -0.0672   0.0154   1.0000
  13.750   1.4714   0.06558   0.05945  -0.0673   0.0152   1.0000
  14.000   1.4634   0.06985   0.06380  -0.0673   0.0150   1.0000
  14.250   1.4549   0.07396   0.06797  -0.0671   0.0148   1.0000
  14.500   1.4500   0.07738   0.07145  -0.0663   0.0146   1.0000
  14.750   1.4510   0.08058   0.07475  -0.0665   0.0144   1.0000
  15.000   1.4521   0.08368   0.07794  -0.0666   0.0143   1.0000
  15.250   1.4532   0.08677   0.08112  -0.0667   0.0140   1.0000
  15.500   1.4546   0.08981   0.08425  -0.0667   0.0138   1.0000
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