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GOE 329 (PFALZ 58) AIRFOIL (goe329-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 329 (PFALZ 58) AIRFOIL (goe329-il)
Reynolds number: 1,000,000
Max Cl/Cd: 125.38 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe329-il-1000000-n5.txt
Download as CSV file: xf-goe329-il-1000000-n5.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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2454   0.09138   0.08912  -0.0436   0.8176   0.0117
  -8.500  -0.2388   0.08816   0.08589  -0.0455   0.8100   0.0120
  -8.250  -0.2419   0.08215   0.07984  -0.0495   0.8033   0.0129
  -8.000  -0.2325   0.07989   0.07758  -0.0512   0.7958   0.0130
  -7.750  -0.2214   0.07756   0.07521  -0.0535   0.7881   0.0132
  -7.500  -0.2070   0.07491   0.07255  -0.0568   0.7809   0.0133
  -7.250  -0.1917   0.07199   0.06958  -0.0605   0.7731   0.0136
  -7.000  -0.1750   0.06853   0.06609  -0.0650   0.7658   0.0139
  -6.750  -0.1567   0.06485   0.06236  -0.0699   0.7580   0.0141
  -6.500  -0.1364   0.06093   0.05837  -0.0749   0.7506   0.0145
  -6.250  -0.1107   0.05386   0.05117  -0.0841   0.7434   0.0157
  -6.000  -0.0884   0.05164   0.04889  -0.0865   0.7353   0.0158
  -5.750  -0.0646   0.04910   0.04626  -0.0893   0.7255   0.0160
  -5.500  -0.0393   0.04626   0.04332  -0.0923   0.7155   0.0163
  -5.250  -0.0130   0.04321   0.04015  -0.0953   0.7046   0.0165
  -5.000   0.0143   0.04008   0.03686  -0.0981   0.6932   0.0168
  -4.750   0.0424   0.03690   0.03352  -0.1006   0.6805   0.0170
  -4.500   0.0718   0.03345   0.02986  -0.1030   0.6662   0.0177
  -4.250   0.1060   0.02692   0.02285  -0.1058   0.6526   0.0186
  -4.000   0.1333   0.02476   0.02046  -0.1068   0.6340   0.0187
  -3.750   0.1604   0.02340   0.01890  -0.1075   0.6147   0.0189
  -3.500   0.1882   0.02191   0.01720  -0.1081   0.5949   0.0190
  -3.250   0.2157   0.02095   0.01606  -0.1086   0.5729   0.0192
  -3.000   0.2437   0.01986   0.01474  -0.1091   0.5511   0.0196
  -2.750   0.2728   0.01821   0.01281  -0.1095   0.5318   0.0197
  -2.500   0.3019   0.01681   0.01112  -0.1099   0.5148   0.0200
  -2.250   0.3311   0.01559   0.00965  -0.1103   0.5006   0.0204
  -2.000   0.3602   0.01453   0.00833  -0.1106   0.4873   0.0207
  -1.750   0.3891   0.01366   0.00724  -0.1108   0.4742   0.0208
  -1.500   0.4180   0.01294   0.00634  -0.1110   0.4620   0.0209
  -1.250   0.4467   0.01242   0.00564  -0.1112   0.4508   0.0213
  -1.000   0.4752   0.01193   0.00500  -0.1114   0.4409   0.0214
  -0.750   0.5039   0.01150   0.00446  -0.1116   0.4328   0.0215
  -0.500   0.5324   0.01121   0.00407  -0.1118   0.4247   0.0217
  -0.250   0.5609   0.01104   0.00383  -0.1119   0.4172   0.0219
   0.000   0.5891   0.01063   0.00337  -0.1122   0.4092   0.0223
   0.250   0.6176   0.01047   0.00319  -0.1124   0.4022   0.0226
   0.500   0.6459   0.01037   0.00306  -0.1126   0.3953   0.0229
   0.750   0.6743   0.01027   0.00295  -0.1128   0.3900   0.0232
   1.000   0.7028   0.01019   0.00285  -0.1130   0.3842   0.0235
   1.250   0.7310   0.01014   0.00277  -0.1132   0.3785   0.0238
   1.500   0.7595   0.01008   0.00270  -0.1134   0.3738   0.0242
   1.750   0.7878   0.01007   0.00267  -0.1136   0.3679   0.0248
   2.250   0.8443   0.01006   0.00263  -0.1140   0.3579   0.0255
   2.500   0.8726   0.01007   0.00264  -0.1141   0.3533   0.0258
   2.750   0.9007   0.01008   0.00263  -0.1143   0.3487   0.0264
   3.000   0.9288   0.01009   0.00265  -0.1145   0.3449   0.0272
   3.250   0.9569   0.01013   0.00270  -0.1147   0.3411   0.0281
   3.500   0.9848   0.01020   0.00277  -0.1148   0.3366   0.0290
   3.750   1.0123   0.01030   0.00285  -0.1149   0.3319   0.0300
   4.000   1.0401   0.01037   0.00294  -0.1150   0.3286   0.0314
   4.250   1.0679   0.01044   0.00302  -0.1151   0.3254   0.0337
   4.750   1.1166   0.00909   0.00351  -0.1144   0.3180   1.0000
   5.000   1.1439   0.00925   0.00364  -0.1145   0.3127   1.0000
   5.250   1.1709   0.00943   0.00378  -0.1145   0.3052   1.0000
   5.500   1.1977   0.00962   0.00394  -0.1145   0.2994   1.0000
   5.750   1.2247   0.00978   0.00409  -0.1145   0.2927   1.0000
   6.000   1.2510   0.01000   0.00428  -0.1144   0.2858   1.0000
   6.250   1.2776   0.01019   0.00445  -0.1144   0.2781   1.0000
   6.500   1.3034   0.01044   0.00466  -0.1143   0.2686   1.0000
   6.750   1.3287   0.01073   0.00490  -0.1141   0.2563   1.0000
   7.000   1.3535   0.01106   0.00516  -0.1138   0.2417   1.0000
   7.250   1.3754   0.01164   0.00557  -0.1131   0.2111   1.0000
   7.500   1.3812   0.01370   0.00695  -0.1100   0.1046   1.0000
   7.750   1.3973   0.01473   0.00777  -0.1084   0.0662   1.0000
   8.000   1.4103   0.01597   0.00875  -0.1063   0.0227   1.0000
   8.250   1.4310   0.01648   0.00925  -0.1053   0.0177   1.0000
   8.500   1.4515   0.01697   0.00974  -0.1044   0.0151   1.0000
   8.750   1.4722   0.01740   0.01020  -0.1035   0.0140   1.0000
   9.000   1.4916   0.01789   0.01071  -0.1023   0.0130   1.0000
   9.250   1.5096   0.01842   0.01127  -0.1010   0.0120   1.0000
   9.500   1.5263   0.01898   0.01185  -0.0994   0.0113   1.0000
   9.750   1.5412   0.01949   0.01241  -0.0975   0.0109   1.0000
  10.000   1.5555   0.02007   0.01304  -0.0955   0.0104   1.0000
  10.250   1.5692   0.02073   0.01373  -0.0936   0.0098   1.0000
  10.500   1.5820   0.02147   0.01451  -0.0917   0.0093   1.0000
  10.750   1.5935   0.02233   0.01542  -0.0897   0.0089   1.0000
  11.000   1.6036   0.02334   0.01648  -0.0877   0.0085   1.0000
  11.250   1.6154   0.02426   0.01746  -0.0861   0.0083   1.0000
  11.500   1.6264   0.02530   0.01856  -0.0845   0.0080   1.0000
  11.750   1.6364   0.02645   0.01977  -0.0829   0.0078   1.0000
  12.000   1.6456   0.02771   0.02110  -0.0814   0.0076   1.0000
  12.250   1.6539   0.02909   0.02255  -0.0799   0.0073   1.0000
  12.500   1.6614   0.03060   0.02412  -0.0785   0.0071   1.0000
  12.750   1.6676   0.03226   0.02585  -0.0772   0.0069   1.0000
  13.000   1.6724   0.03412   0.02778  -0.0759   0.0067   1.0000
  13.250   1.6754   0.03624   0.02996  -0.0747   0.0064   1.0000
  13.500   1.6746   0.03879   0.03261  -0.0735   0.0062   1.0000
  13.750   1.6749   0.04134   0.03525  -0.0725   0.0061   1.0000
  14.000   1.6758   0.04392   0.03792  -0.0717   0.0060   1.0000
  14.250   1.6749   0.04678   0.04088  -0.0711   0.0059   1.0000
  14.500   1.6725   0.04995   0.04414  -0.0707   0.0058   1.0000
  14.750   1.6686   0.05345   0.04775  -0.0705   0.0058   1.0000
  15.000   1.6642   0.05715   0.05155  -0.0704   0.0057   1.0000
  15.250   1.6580   0.06117   0.05568  -0.0706   0.0056   1.0000
  15.500   1.6508   0.06546   0.06008  -0.0710   0.0055   1.0000
  15.750   1.6430   0.06993   0.06465  -0.0715   0.0054   1.0000
  16.000   1.6337   0.07465   0.06948  -0.0722   0.0054   1.0000
  16.250   1.6240   0.07947   0.07441  -0.0729   0.0053   1.0000
  16.500   1.6139   0.08442   0.07946  -0.0737   0.0052   1.0000
  16.750   1.6035   0.08944   0.08458  -0.0747   0.0052   1.0000
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