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GOE 326 (PFALZ 55) AIRFOIL (goe326-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 326 (PFALZ 55) AIRFOIL (goe326-il)
Reynolds number: 500,000
Max Cl/Cd: 100.08 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe326-il-500000-n5.txt
Download as CSV file: xf-goe326-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 326 (PFALZ 55) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3478   0.09610   0.09393  -0.0211   1.0000   0.0090
  -8.500  -0.3440   0.09250   0.09036  -0.0229   1.0000   0.0091
  -8.250  -0.3411   0.08890   0.08678  -0.0246   1.0000   0.0092
  -8.000  -0.3309   0.08415   0.08203  -0.0295   0.9687   0.0095
  -7.500  -0.3107   0.07150   0.06927  -0.0441   0.9129   0.0106
  -7.250  -0.2943   0.06900   0.06670  -0.0471   0.8980   0.0109
  -7.000  -0.2766   0.06634   0.06397  -0.0504   0.8847   0.0113
  -6.750  -0.2578   0.06278   0.06034  -0.0547   0.8720   0.0119
  -6.500  -0.2369   0.05731   0.05476  -0.0612   0.8594   0.0126
  -6.250  -0.2109   0.04697   0.04416  -0.0723   0.8473   0.0142
  -6.000  -0.1869   0.04539   0.04248  -0.0738   0.8344   0.0147
  -5.500  -0.1308   0.03053   0.02685  -0.0838   0.8099   0.0188
  -5.250  -0.1055   0.03010   0.02632  -0.0840   0.7976   0.0193
  -5.000  -0.0798   0.02930   0.02540  -0.0843   0.7866   0.0201
  -4.750  -0.0533   0.02686   0.02270  -0.0851   0.7763   0.0213
  -4.500  -0.0252   0.02030   0.01535  -0.0860   0.7682   0.0245
  -4.250   0.0003   0.01811   0.01279  -0.0864   0.7594   0.0255
  -4.000   0.0274   0.01755   0.01210  -0.0864   0.7503   0.0261
  -3.750   0.0546   0.01712   0.01154  -0.0864   0.7419   0.0270
  -3.500   0.0819   0.01630   0.01053  -0.0864   0.7331   0.0278
  -3.250   0.1095   0.01521   0.00918  -0.0864   0.7248   0.0284
  -3.000   0.1371   0.01425   0.00797  -0.0863   0.7159   0.0290
  -2.750   0.1650   0.01346   0.00699  -0.0863   0.7073   0.0297
  -2.500   0.1927   0.01291   0.00628  -0.0862   0.6987   0.0306
  -2.250   0.2207   0.01229   0.00552  -0.0861   0.6894   0.0311
  -2.000   0.2486   0.01181   0.00492  -0.0860   0.6798   0.0316
  -1.750   0.2764   0.01145   0.00444  -0.0859   0.6691   0.0320
  -1.500   0.3043   0.01115   0.00406  -0.0858   0.6562   0.0324
  -1.250   0.3320   0.01090   0.00373  -0.0857   0.6410   0.0326
  -1.000   0.3593   0.01037   0.00309  -0.0856   0.6218   0.0334
  -0.750   0.3864   0.01011   0.00271  -0.0854   0.5960   0.0340
  -0.500   0.4134   0.00999   0.00246  -0.0852   0.5700   0.0347
  -0.250   0.4405   0.00996   0.00232  -0.0851   0.5489   0.0358
   0.000   0.4679   0.00993   0.00222  -0.0850   0.5328   0.0369
   0.250   0.4953   0.00989   0.00211  -0.0849   0.5197   0.0377
   0.500   0.5229   0.00986   0.00202  -0.0848   0.5082   0.0389
   0.750   0.5506   0.00984   0.00196  -0.0847   0.4974   0.0405
   1.000   0.5781   0.00986   0.00192  -0.0847   0.4853   0.0422
   1.250   0.6057   0.00989   0.00190  -0.0846   0.4738   0.0443
   1.500   0.6333   0.00990   0.00188  -0.0846   0.4631   0.0494
   1.750   0.6610   0.00993   0.00190  -0.0845   0.4534   0.0552
   2.000   0.6886   0.00997   0.00194  -0.0845   0.4426   0.0682
   2.500   0.7405   0.00822   0.00222  -0.0843   0.4203   1.0000
   2.750   0.7678   0.00836   0.00230  -0.0842   0.4104   1.0000
   3.000   0.7950   0.00852   0.00238  -0.0840   0.3993   1.0000
   3.250   0.8219   0.00870   0.00249  -0.0839   0.3858   1.0000
   3.500   0.8488   0.00888   0.00261  -0.0838   0.3733   1.0000
   3.750   0.8758   0.00906   0.00273  -0.0836   0.3622   1.0000
   4.000   0.9026   0.00924   0.00287  -0.0835   0.3522   1.0000
   4.250   0.9293   0.00945   0.00304  -0.0834   0.3418   1.0000
   4.500   0.9558   0.00966   0.00320  -0.0832   0.3301   1.0000
   4.750   0.9823   0.00987   0.00338  -0.0830   0.3191   1.0000
   5.000   1.0087   0.01009   0.00358  -0.0829   0.3090   1.0000
   5.250   1.0348   0.01034   0.00380  -0.0826   0.2974   1.0000
   5.500   1.0606   0.01061   0.00402  -0.0824   0.2843   1.0000
   5.750   1.0855   0.01098   0.00430  -0.0821   0.2591   1.0000
   6.000   1.1095   0.01146   0.00462  -0.0816   0.2284   1.0000
   6.250   1.1320   0.01210   0.00503  -0.0810   0.1865   1.0000
   6.500   1.1509   0.01318   0.00572  -0.0800   0.1240   1.0000
   6.750   1.1741   0.01371   0.00619  -0.0795   0.1089   1.0000
   7.000   1.1975   0.01419   0.00663  -0.0789   0.0986   1.0000
   7.250   1.2211   0.01463   0.00705  -0.0784   0.0871   1.0000
   7.500   1.2426   0.01529   0.00756  -0.0777   0.0636   1.0000
   7.750   1.2573   0.01667   0.00865  -0.0761   0.0183   1.0000
   8.000   1.2786   0.01728   0.00930  -0.0752   0.0144   1.0000
   8.250   1.3006   0.01779   0.00988  -0.0744   0.0128   1.0000
   8.500   1.3217   0.01835   0.01053  -0.0735   0.0115   1.0000
   8.750   1.3414   0.01903   0.01128  -0.0725   0.0104   1.0000
   9.000   1.3593   0.01983   0.01220  -0.0712   0.0096   1.0000
   9.250   1.3785   0.02046   0.01291  -0.0701   0.0091   1.0000
   9.500   1.3964   0.02116   0.01369  -0.0688   0.0085   1.0000
   9.750   1.4131   0.02190   0.01450  -0.0674   0.0079   1.0000
  10.000   1.4280   0.02272   0.01538  -0.0658   0.0074   1.0000
  10.250   1.4374   0.02373   0.01647  -0.0633   0.0070   1.0000
  10.500   1.4431   0.02498   0.01782  -0.0605   0.0067   1.0000
  10.750   1.4523   0.02605   0.01900  -0.0584   0.0065   1.0000
  11.000   1.4600   0.02730   0.02036  -0.0564   0.0063   1.0000
  11.250   1.4662   0.02874   0.02191  -0.0545   0.0061   1.0000
  11.500   1.4711   0.03038   0.02365  -0.0527   0.0059   1.0000
  11.750   1.4751   0.03219   0.02558  -0.0512   0.0058   1.0000
  12.000   1.4783   0.03419   0.02769  -0.0499   0.0056   1.0000
  12.250   1.4810   0.03636   0.02995  -0.0488   0.0054   1.0000
  12.500   1.4835   0.03866   0.03235  -0.0481   0.0053   1.0000
  12.750   1.4847   0.04121   0.03500  -0.0475   0.0051   1.0000
  13.000   1.4840   0.04406   0.03796  -0.0471   0.0050   1.0000
  13.250   1.4801   0.04740   0.04142  -0.0469   0.0049   1.0000
  13.500   1.4718   0.05136   0.04551  -0.0469   0.0047   1.0000
  13.750   1.4653   0.05529   0.04955  -0.0472   0.0047   1.0000
  14.000   1.4615   0.05899   0.05339  -0.0476   0.0046   1.0000
  14.250   1.4558   0.06305   0.05758  -0.0482   0.0045   1.0000
  14.500   1.4491   0.06742   0.06207  -0.0491   0.0045   1.0000
  14.750   1.4417   0.07197   0.06675  -0.0501   0.0044   1.0000
  15.000   1.4339   0.07664   0.07155  -0.0512   0.0043   1.0000
  15.250   1.4257   0.08146   0.07649  -0.0524   0.0043   1.0000
  15.500   1.4175   0.08637   0.08152  -0.0538   0.0042   1.0000
  15.750   1.4091   0.09134   0.08661  -0.0552   0.0042   1.0000
  16.000   1.4006   0.09640   0.09179  -0.0568   0.0041   1.0000
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