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GOE 330 (PFALZ 59) AIRFOIL (goe330-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 330 (PFALZ 59) AIRFOIL (goe330-il)
Reynolds number: 1,000,000
Max Cl/Cd: 128.06 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe330-il-1000000.txt
Download as CSV file: xf-goe330-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 330 (PFALZ 59) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.1656   0.08651   0.08481  -0.0695   0.9413   0.0168
  -8.500  -0.1615   0.08313   0.08138  -0.0711   0.9247   0.0168
  -8.250  -0.1581   0.07953   0.07773  -0.0713   0.9113   0.0171
  -8.000  -0.1481   0.07754   0.07570  -0.0717   0.8990   0.0173
  -7.750  -0.1384   0.07529   0.07341  -0.0730   0.8873   0.0176
  -7.500  -0.1283   0.07281   0.07088  -0.0752   0.8769   0.0180
  -7.250  -0.1147   0.06988   0.06790  -0.0786   0.8680   0.0186
  -6.500  -0.0530   0.05163   0.04941  -0.1047   0.8459   0.0211
  -6.250  -0.0340   0.04963   0.04736  -0.1062   0.8396   0.0214
  -6.000  -0.0129   0.04756   0.04523  -0.1081   0.8337   0.0217
  -5.750   0.0103   0.04510   0.04271  -0.1106   0.8275   0.0222
  -5.500   0.0352   0.04218   0.03967  -0.1137   0.8217   0.0233
  -5.250   0.0731   0.03571   0.03291  -0.1198   0.8161   0.0255
  -5.000   0.0922   0.02911   0.02601  -0.1228   0.8100   0.0262
  -4.750   0.1159   0.02780   0.02461  -0.1232   0.8038   0.0266
  -4.500   0.1405   0.02646   0.02318  -0.1237   0.7970   0.0272
  -4.250   0.1653   0.02495   0.02152  -0.1240   0.7900   0.0281
  -4.000   0.1957   0.02339   0.01971  -0.1238   0.7828   0.0313
  -3.000   0.2925   0.01347   0.00858  -0.1229   0.7480   0.0308
  -2.750   0.3182   0.01202   0.00687  -0.1224   0.7366   0.0307
  -2.500   0.3443   0.01112   0.00576  -0.1220   0.7222   0.0307
  -2.250   0.3703   0.01050   0.00497  -0.1216   0.7041   0.0308
  -1.750   0.4218   0.00970   0.00385  -0.1206   0.6672   0.0310
  -1.500   0.4479   0.00942   0.00345  -0.1202   0.6532   0.0311
  -1.250   0.4746   0.00929   0.00324  -0.1198   0.6410   0.0314
  -1.000   0.5003   0.00874   0.00259  -0.1194   0.6296   0.0322
  -0.750   0.5264   0.00848   0.00225  -0.1190   0.6185   0.0330
  -0.500   0.5526   0.00837   0.00207  -0.1187   0.6073   0.0338
  -0.250   0.5797   0.00828   0.00195  -0.1185   0.5967   0.0346
   0.000   0.6066   0.00823   0.00185  -0.1183   0.5857   0.0354
   0.250   0.6334   0.00820   0.00177  -0.1180   0.5739   0.0363
   0.500   0.6601   0.00820   0.00171  -0.1178   0.5606   0.0373
   0.750   0.6868   0.00822   0.00166  -0.1175   0.5436   0.0385
   1.000   0.7128   0.00826   0.00162  -0.1171   0.5190   0.0424
   1.250   0.7377   0.00841   0.00168  -0.1166   0.4875   0.0526
   1.500   0.7624   0.00860   0.00178  -0.1160   0.4595   0.0736
   1.750   0.7877   0.00878   0.00187  -0.1156   0.4407   0.0820
   2.000   0.8136   0.00889   0.00195  -0.1153   0.4278   0.0919
   2.250   0.8398   0.00894   0.00205  -0.1151   0.4180   0.1303
   2.500   0.8617   0.00807   0.00234  -0.1146   0.4095   0.6686
   3.250   0.9515   0.00788   0.00271  -0.1161   0.3875   1.0000
   3.500   0.9767   0.00804   0.00282  -0.1157   0.3807   1.0000
   3.750   1.0021   0.00818   0.00293  -0.1152   0.3749   1.0000
   4.000   1.0279   0.00831   0.00303  -0.1149   0.3694   1.0000
   4.250   1.0529   0.00849   0.00317  -0.1144   0.3633   1.0000
   4.500   1.0787   0.00861   0.00329  -0.1141   0.3583   1.0000
   4.750   1.1043   0.00875   0.00341  -0.1138   0.3531   1.0000
   5.000   1.1292   0.00893   0.00356  -0.1133   0.3475   1.0000
   5.250   1.1549   0.00906   0.00369  -0.1130   0.3405   1.0000
   5.500   1.1795   0.00927   0.00385  -0.1125   0.3325   1.0000
   5.750   1.2050   0.00941   0.00399  -0.1122   0.3257   1.0000
   6.000   1.2292   0.00964   0.00418  -0.1116   0.3156   1.0000
   6.250   1.2540   0.00982   0.00434  -0.1112   0.3063   1.0000
   6.500   1.2780   0.01005   0.00454  -0.1107   0.2946   1.0000
   6.750   1.3010   0.01035   0.00476  -0.1100   0.2779   1.0000
   7.000   1.3228   0.01073   0.00504  -0.1091   0.2587   1.0000
   7.250   1.3422   0.01126   0.00541  -0.1078   0.2286   1.0000
   7.500   1.3567   0.01212   0.00600  -0.1058   0.1853   1.0000
   7.750   1.3731   0.01283   0.00655  -0.1041   0.1609   1.0000
   8.000   1.3891   0.01355   0.00711  -0.1023   0.1343   1.0000
   8.250   1.3792   0.01576   0.00872  -0.0963   0.0373   1.0000
   8.500   1.3900   0.01665   0.00954  -0.0936   0.0209   1.0000
   8.750   1.4065   0.01719   0.01012  -0.0919   0.0188   1.0000
   9.000   1.4207   0.01788   0.01084  -0.0899   0.0167   1.0000
   9.250   1.4369   0.01844   0.01145  -0.0883   0.0158   1.0000
   9.500   1.4524   0.01905   0.01211  -0.0867   0.0149   1.0000
   9.750   1.4666   0.01975   0.01284  -0.0849   0.0141   1.0000
  10.000   1.4785   0.02062   0.01376  -0.0829   0.0133   1.0000
  10.250   1.4858   0.02181   0.01505  -0.0803   0.0126   1.0000
  10.500   1.4993   0.02261   0.01590  -0.0788   0.0123   1.0000
  10.750   1.5114   0.02353   0.01688  -0.0771   0.0119   1.0000
  11.000   1.5223   0.02454   0.01796  -0.0754   0.0114   1.0000
  11.250   1.5326   0.02564   0.01911  -0.0737   0.0110   1.0000
  11.500   1.5420   0.02683   0.02036  -0.0721   0.0106   1.0000
  11.750   1.5486   0.02829   0.02187  -0.0703   0.0102   1.0000
  12.000   1.5494   0.03028   0.02396  -0.0681   0.0098   1.0000
  12.250   1.5399   0.03323   0.02706  -0.0654   0.0095   1.0000
  12.500   1.5467   0.03487   0.02878  -0.0642   0.0094   1.0000
  12.750   1.5517   0.03673   0.03071  -0.0630   0.0092   1.0000
  13.000   1.5545   0.03884   0.03290  -0.0618   0.0091   1.0000
  13.250   1.5558   0.04120   0.03535  -0.0607   0.0089   1.0000
  13.500   1.5556   0.04383   0.03808  -0.0597   0.0087   1.0000
  13.750   1.5544   0.04670   0.04104  -0.0590   0.0085   1.0000
  14.000   1.5523   0.04978   0.04422  -0.0585   0.0084   1.0000
  14.250   1.5498   0.05306   0.04759  -0.0582   0.0082   1.0000
  14.500   1.5457   0.05662   0.05124  -0.0580   0.0081   1.0000
  14.750   1.5412   0.06029   0.05500  -0.0580   0.0079   1.0000
  15.000   1.5359   0.06415   0.05895  -0.0581   0.0078   1.0000
  15.250   1.5292   0.06831   0.06321  -0.0584   0.0077   1.0000
  15.500   1.5220   0.07257   0.06755  -0.0588   0.0076   1.0000
  15.750   1.5134   0.07710   0.07218  -0.0594   0.0075   1.0000
  16.000   1.5032   0.08196   0.07713  -0.0601   0.0074   1.0000
  16.250   1.4914   0.08709   0.08236  -0.0610   0.0073   1.0000
  16.500   1.4770   0.09250   0.08785  -0.0618   0.0072   1.0000
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