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GOE 332 (PFALZ 61) AIRFOIL (goe332-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 332 (PFALZ 61) AIRFOIL (goe332-il)
Reynolds number: 1,000,000
Max Cl/Cd: 131.19 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe332-il-1000000-n5.txt
Download as CSV file: xf-goe332-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 332 (PFALZ 61) 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.1353   0.09560   0.09303  -0.0805   0.8068   0.0144
 -10.000  -0.1293   0.09252   0.08992  -0.0820   0.7965   0.0148
  -9.750  -0.1397   0.08537   0.08273  -0.0856   0.7884   0.0162
  -9.500  -0.1304   0.08314   0.08047  -0.0869   0.7795   0.0163
  -9.250  -0.1203   0.08109   0.07838  -0.0882   0.7710   0.0164
  -9.000  -0.1104   0.07891   0.07618  -0.0895   0.7620   0.0166
  -8.750  -0.1014   0.07652   0.07376  -0.0910   0.7535   0.0168
  -8.500  -0.0935   0.07383   0.07104  -0.0928   0.7444   0.0170
  -8.250  -0.0864   0.07096   0.06815  -0.0949   0.7363   0.0172
  -8.000  -0.0803   0.06777   0.06493  -0.0979   0.7273   0.0175
  -7.750  -0.0698   0.06348   0.06061  -0.1034   0.7192   0.0180
  -7.500  -0.0667   0.04887   0.04586  -0.1229   0.7116   0.0195
  -7.250  -0.0762   0.01865   0.01414  -0.1450   0.7075   0.0217
  -7.000  -0.0525   0.01687   0.01205  -0.1453   0.6993   0.0220
  -6.750  -0.0276   0.01571   0.01064  -0.1453   0.6913   0.0222
  -6.500  -0.0015   0.01482   0.00955  -0.1453   0.6837   0.0224
  -6.000   0.0516   0.01356   0.00795  -0.1452   0.6690   0.0228
  -5.750   0.0787   0.01318   0.00745  -0.1452   0.6619   0.0229
  -5.500   0.1062   0.01286   0.00703  -0.1452   0.6556   0.0231
  -5.250   0.1329   0.01208   0.00609  -0.1452   0.6493   0.0234
  -4.750   0.1877   0.01129   0.00513  -0.1452   0.6376   0.0239
  -4.500   0.2154   0.01103   0.00481  -0.1452   0.6318   0.0241
  -4.250   0.2429   0.01081   0.00452  -0.1451   0.6262   0.0243
  -4.000   0.2710   0.01057   0.00424  -0.1452   0.6213   0.0245
  -3.750   0.2990   0.01036   0.00399  -0.1452   0.6158   0.0248
  -3.250   0.3547   0.00999   0.00351  -0.1451   0.6040   0.0253
  -3.000   0.3825   0.00983   0.00329  -0.1451   0.5973   0.0256
  -2.750   0.4103   0.00968   0.00310  -0.1451   0.5918   0.0259
  -2.500   0.4385   0.00953   0.00291  -0.1451   0.5873   0.0262
  -2.250   0.4666   0.00940   0.00275  -0.1452   0.5824   0.0265
  -2.000   0.4944   0.00930   0.00261  -0.1451   0.5775   0.0268
  -1.750   0.5228   0.00920   0.00250  -0.1452   0.5732   0.0272
  -1.500   0.5510   0.00914   0.00242  -0.1453   0.5685   0.0275
  -1.250   0.5789   0.00900   0.00224  -0.1453   0.5634   0.0282
  -1.000   0.6069   0.00891   0.00214  -0.1453   0.5586   0.0288
  -0.750   0.6351   0.00884   0.00207  -0.1453   0.5534   0.0294
  -0.500   0.6631   0.00881   0.00202  -0.1454   0.5482   0.0301
  -0.250   0.6908   0.00879   0.00198  -0.1453   0.5431   0.0308
   0.000   0.7190   0.00876   0.00195  -0.1454   0.5374   0.0315
   0.250   0.7466   0.00877   0.00192  -0.1453   0.5306   0.0323
   0.500   0.7744   0.00876   0.00191  -0.1453   0.5247   0.0333
   0.750   0.8022   0.00876   0.00190  -0.1453   0.5181   0.0357
   1.000   0.8296   0.00879   0.00192  -0.1453   0.5115   0.0389
   1.250   0.8573   0.00878   0.00193  -0.1453   0.5040   0.0494
   1.500   0.8843   0.00875   0.00201  -0.1452   0.4955   0.1033
   1.750   0.9116   0.00880   0.00207  -0.1452   0.4865   0.1213
   2.000   0.9385   0.00888   0.00214  -0.1450   0.4781   0.1329
   2.250   0.9654   0.00894   0.00222  -0.1449   0.4691   0.1467
   2.500   0.9919   0.00904   0.00231  -0.1447   0.4580   0.1638
   2.750   1.0178   0.00908   0.00244  -0.1445   0.4441   0.2350
   3.000   1.0390   0.00806   0.00282  -0.1438   0.4295   0.8683
   3.250   1.0624   0.00810   0.00292  -0.1428   0.4157   1.0000
   3.500   1.0880   0.00831   0.00306  -0.1424   0.4031   1.0000
   3.750   1.1138   0.00849   0.00318  -0.1421   0.3925   1.0000
   4.000   1.1393   0.00870   0.00333  -0.1417   0.3826   1.0000
   4.250   1.1646   0.00890   0.00348  -0.1414   0.3724   1.0000
   4.500   1.1896   0.00912   0.00364  -0.1409   0.3611   1.0000
   4.750   1.2142   0.00937   0.00382  -0.1404   0.3501   1.0000
   5.000   1.2389   0.00959   0.00400  -0.1400   0.3404   1.0000
   5.250   1.2639   0.00980   0.00418  -0.1396   0.3330   1.0000
   5.500   1.2883   0.01003   0.00437  -0.1391   0.3248   1.0000
   5.750   1.3129   0.01024   0.00455  -0.1386   0.3182   1.0000
   6.000   1.3370   0.01047   0.00476  -0.1380   0.3103   1.0000
   6.250   1.3607   0.01071   0.00498  -0.1374   0.3033   1.0000
   6.500   1.3843   0.01095   0.00519  -0.1368   0.2953   1.0000
   6.750   1.4069   0.01123   0.00545  -0.1360   0.2862   1.0000
   7.000   1.4282   0.01158   0.00573  -0.1349   0.2744   1.0000
   7.250   1.4489   0.01193   0.00603  -0.1338   0.2615   1.0000
   7.500   1.4691   0.01228   0.00633  -0.1326   0.2491   1.0000
   7.750   1.4844   0.01279   0.00674  -0.1305   0.2307   1.0000
   8.000   1.4987   0.01334   0.00719  -0.1282   0.2103   1.0000
   8.250   1.5100   0.01406   0.00778  -0.1255   0.1876   1.0000
   8.500   1.5215   0.01478   0.00839  -0.1228   0.1677   1.0000
   8.750   1.5341   0.01545   0.00900  -0.1205   0.1529   1.0000
   9.000   1.5467   0.01615   0.00963  -0.1182   0.1391   1.0000
   9.250   1.5537   0.01714   0.01049  -0.1151   0.1174   1.0000
   9.500   1.5531   0.01860   0.01177  -0.1111   0.0870   1.0000
   9.750   1.5642   0.01946   0.01261  -0.1089   0.0787   1.0000
  10.000   1.5745   0.02041   0.01355  -0.1067   0.0716   1.0000
  10.250   1.5858   0.02133   0.01447  -0.1048   0.0638   1.0000
  10.500   1.5776   0.02362   0.01657  -0.1008   0.0328   1.0000
  10.750   1.5818   0.02520   0.01814  -0.0985   0.0237   1.0000
  11.000   1.5902   0.02654   0.01950  -0.0968   0.0200   1.0000
  11.250   1.5987   0.02793   0.02092  -0.0952   0.0176   1.0000
  11.500   1.6082   0.02927   0.02230  -0.0938   0.0161   1.0000
  11.750   1.6163   0.03076   0.02383  -0.0924   0.0149   1.0000
  12.000   1.6242   0.03230   0.02541  -0.0911   0.0139   1.0000
  12.250   1.6326   0.03383   0.02700  -0.0899   0.0133   1.0000
  12.500   1.6398   0.03550   0.02872  -0.0887   0.0127   1.0000
  12.750   1.6458   0.03731   0.03058  -0.0875   0.0121   1.0000
  13.000   1.6509   0.03925   0.03258  -0.0864   0.0115   1.0000
  13.250   1.6552   0.04132   0.03470  -0.0853   0.0111   1.0000
  13.500   1.6608   0.04329   0.03674  -0.0844   0.0108   1.0000
  13.750   1.6655   0.04539   0.03890  -0.0835   0.0104   1.0000
  14.000   1.6692   0.04763   0.04121  -0.0826   0.0101   1.0000
  14.250   1.6721   0.05002   0.04366  -0.0818   0.0097   1.0000
  14.500   1.6741   0.05255   0.04626  -0.0811   0.0094   1.0000
  14.750   1.6748   0.05526   0.04903  -0.0805   0.0090   1.0000
  15.000   1.6743   0.05813   0.05197  -0.0798   0.0088   1.0000
  15.250   1.6739   0.06107   0.05498  -0.0793   0.0085   1.0000
  15.500   1.6745   0.06392   0.05791  -0.0789   0.0084   1.0000
  15.750   1.6738   0.06697   0.06105  -0.0785   0.0082   1.0000
  16.000   1.6726   0.07011   0.06426  -0.0783   0.0081   1.0000
  16.250   1.6710   0.07333   0.06756  -0.0780   0.0079   1.0000
  16.500   1.6686   0.07669   0.07101  -0.0779   0.0077   1.0000
  16.750   1.6652   0.08025   0.07465  -0.0779   0.0076   1.0000
  17.000   1.6614   0.08391   0.07839  -0.0780   0.0074   1.0000
  17.250   1.6567   0.08770   0.08226  -0.0782   0.0073   1.0000
  17.500   1.6517   0.09156   0.08620  -0.0784   0.0071   1.0000
  17.750   1.6461   0.09557   0.09029  -0.0788   0.0070   1.0000
  18.000   1.6395   0.09977   0.09459  -0.0793   0.0068   1.0000
  18.250   1.6319   0.10418   0.09908  -0.0800   0.0067   1.0000
  18.500   1.6231   0.10877   0.10375  -0.0808   0.0065   1.0000
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