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GOE 332 (PFALZ 61) AIRFOIL (goe332-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 332 (PFALZ 61) AIRFOIL (goe332-il)
Reynolds number: 50,000
Max Cl/Cd: 29.52 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe332-il-50000-n5.txt
Download as CSV file: xf-goe332-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2262   0.11379   0.10741  -0.0453   0.9767   0.1134
  -8.000  -0.2247   0.11247   0.10611  -0.0513   0.9643   0.1171
  -7.750  -0.2244   0.11130   0.10496  -0.0601   0.9486   0.1181
  -7.500  -0.1977   0.10472   0.09837  -0.0565   0.9467   0.1206
  -7.250  -0.1796   0.10099   0.09462  -0.0583   0.9389   0.1236
  -7.000  -0.1673   0.09795   0.09156  -0.0610   0.9287   0.1267
  -6.750  -0.1527   0.09487   0.08846  -0.0668   0.9190   0.1311
  -6.500  -0.1388   0.09260   0.08609  -0.0790   0.9066   0.1337
  -6.000  -0.1049   0.08463   0.07815  -0.0778   0.8932   0.1381
  -5.750  -0.0886   0.08178   0.07525  -0.0802   0.8849   0.1436
  -5.500  -0.0631   0.07863   0.07193  -0.0918   0.8759   0.1500
  -5.250  -0.0498   0.07531   0.06862  -0.0903   0.8683   0.1519
  -4.750   0.0158   0.06349   0.05610  -0.1072   0.8537   0.0896
  -4.500   0.0364   0.06080   0.05335  -0.1079   0.8465   0.0862
  -4.250   0.0704   0.05709   0.04943  -0.1124   0.8422   0.0840
  -4.000   0.0897   0.05467   0.04682  -0.1139   0.8329   0.0837
  -3.750   0.1240   0.05144   0.04329  -0.1178   0.8276   0.0834
  -3.500   0.1593   0.04823   0.03974  -0.1216   0.8227   0.0817
  -3.250   0.1832   0.04590   0.03708  -0.1228   0.8142   0.0802
  -3.000   0.2224   0.04290   0.03359  -0.1263   0.8099   0.0790
  -2.750   0.2509   0.04097   0.03126  -0.1275   0.8030   0.0786
  -2.500   0.2794   0.03953   0.02954  -0.1284   0.7962   0.0798
  -2.250   0.3171   0.03792   0.02760  -0.1305   0.7921   0.0826
  -2.000   0.3395   0.03706   0.02643  -0.1301   0.7837   0.0844
  -1.750   0.3727   0.03571   0.02472  -0.1311   0.7781   0.0857
  -1.500   0.4120   0.03423   0.02281  -0.1328   0.7743   0.0874
  -1.250   0.4299   0.03394   0.02225  -0.1313   0.7648   0.0889
  -1.000   0.4629   0.03317   0.02144  -0.1321   0.7597   0.0929
  -0.750   0.4872   0.03293   0.02105  -0.1315   0.7524   0.0987
  -0.500   0.5152   0.03253   0.02044  -0.1312   0.7454   0.1046
  -0.250   0.5521   0.03176   0.01954  -0.1322   0.7413   0.1129
   0.000   0.5684   0.03199   0.01972  -0.1305   0.7314   0.1223
   0.250   0.6024   0.03139   0.01905  -0.1311   0.7263   0.1460
   0.500   0.6233   0.03132   0.01907  -0.1301   0.7178   0.1814
   0.750   0.6534   0.03057   0.01877  -0.1307   0.7115   0.2686
   1.000   0.6757   0.02879   0.01859  -0.1290   0.7053   1.0000
   1.250   0.6966   0.02932   0.01881  -0.1278   0.6964   1.0000
   1.500   0.7331   0.02914   0.01830  -0.1286   0.6918   1.0000
   2.000   0.7811   0.02987   0.01866  -0.1272   0.6761   1.0000
   2.250   0.7941   0.03076   0.01946  -0.1251   0.6655   1.0000
   2.500   0.8283   0.03064   0.01916  -0.1257   0.6603   1.0000
   2.750   0.8415   0.03154   0.02001  -0.1237   0.6500   1.0000
   3.000   0.8744   0.03147   0.01980  -0.1241   0.6445   1.0000
   3.250   0.8881   0.03237   0.02068  -0.1222   0.6343   1.0000
   3.500   0.9196   0.03235   0.02056  -0.1223   0.6284   1.0000
   3.750   0.9333   0.03328   0.02147  -0.1205   0.6186   1.0000
   4.000   0.9636   0.03330   0.02143  -0.1205   0.6123   1.0000
   4.250   0.9769   0.03425   0.02239  -0.1186   0.6024   1.0000
   4.500   1.0058   0.03435   0.02244  -0.1185   0.5960   1.0000
   4.750   1.0180   0.03537   0.02350  -0.1165   0.5861   1.0000
   5.000   1.0465   0.03547   0.02357  -0.1163   0.5795   1.0000
   5.250   1.0562   0.03664   0.02479  -0.1141   0.5695   1.0000
   5.500   1.0847   0.03674   0.02489  -0.1139   0.5630   1.0000
   5.750   1.0906   0.03810   0.02631  -0.1113   0.5527   1.0000
   6.000   1.1206   0.03810   0.02632  -0.1112   0.5465   1.0000
   6.250   1.1206   0.03979   0.02808  -0.1080   0.5359   1.0000
   6.500   1.1520   0.03967   0.02800  -0.1080   0.5302   1.0000
   6.750   1.1485   0.04169   0.03010  -0.1047   0.5193   1.0000
   7.000   1.1813   0.04143   0.02987  -0.1048   0.5140   1.0000
   7.250   1.1736   0.04390   0.03244  -0.1014   0.5028   1.0000
   7.500   1.2085   0.04339   0.03199  -0.1015   0.4979   1.0000
   7.750   1.1967   0.04634   0.03505  -0.0982   0.4864   1.0000
   8.000   1.2337   0.04556   0.03432  -0.0983   0.4819   1.0000
   8.250   1.2184   0.04895   0.03782  -0.0951   0.4700   1.0000
   8.500   1.2590   0.04769   0.03663  -0.0952   0.4659   1.0000
   8.750   1.2397   0.05160   0.04066  -0.0921   0.4535   1.0000
   9.000   1.2842   0.04981   0.03893  -0.0921   0.4497   1.0000
   9.250   1.2594   0.05448   0.04372  -0.0893   0.4371   1.0000
   9.500   1.3058   0.05235   0.04169  -0.0892   0.4336   1.0000
   9.750   1.2751   0.05788   0.04735  -0.0866   0.4208   1.0000
  10.000   1.3220   0.05554   0.04511  -0.0862   0.4176   1.0000
  10.250   1.2849   0.06212   0.05182  -0.0840   0.4045   1.0000
  10.500   1.3318   0.05957   0.04937  -0.0834   0.4016   1.0000
  10.750   1.2908   0.06699   0.05692  -0.0818   0.3881   1.0000
  11.250   1.2937   0.07239   0.06255  -0.0798   0.3716   1.0000
  11.750   1.2384   0.08637   0.07672  -0.0797   0.3470   1.0000
  12.000   1.2542   0.08716   0.07767  -0.0787   0.3411   1.0000
  12.250   1.2945   0.08420   0.07488  -0.0768   0.3385   1.0000
  12.750   1.2257   0.10119   0.09200  -0.0788   0.3113   1.0000
  13.000   1.2618   0.09813   0.08911  -0.0766   0.3077   1.0000
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