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GOE 573 AIRFOIL (goe573-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 573 AIRFOIL (goe573-il)
Reynolds number: 1,000,000
Max Cl/Cd: 130.24 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe573-il-1000000.txt
Download as CSV file: xf-goe573-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 573 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.0016   0.09236   0.08972  -0.1093   0.7751   0.0178
 -10.500   0.0723   0.07503   0.07207  -0.1136   0.6788   0.0180
 -10.250   0.0826   0.07296   0.06992  -0.1134   0.6644   0.0182
 -10.000   0.0883   0.07036   0.06727  -0.1138   0.6525   0.0183
  -9.750   0.0970   0.06846   0.06533  -0.1141   0.6414   0.0187
  -9.500   0.0999   0.06551   0.06236  -0.1147   0.6336   0.0189
  -9.250   0.1056   0.06317   0.05999  -0.1152   0.6245   0.0195
  -9.000   0.1078   0.06024   0.05704  -0.1159   0.6167   0.0203
  -8.750   0.0924   0.05468   0.05150  -0.1191   0.6137   0.0216
  -8.500   0.0888   0.05106   0.04787  -0.1203   0.6075   0.0216
  -8.250   0.0821   0.04737   0.04417  -0.1219   0.6020   0.0217
  -8.000   0.0715   0.04403   0.04085  -0.1233   0.5969   0.0217
  -7.750   0.0538   0.04062   0.03742  -0.1222   0.5917   0.0217
  -7.500   0.0332   0.03539   0.03215  -0.1218   0.5879   0.0220
  -7.250   0.0380   0.03348   0.03021  -0.1208   0.5813   0.0222
  -7.000   0.0467   0.03213   0.02881  -0.1198   0.5739   0.0225
  -6.750   0.0534   0.03005   0.02667  -0.1190   0.5680   0.0227
  -6.500   0.0612   0.02806   0.02461  -0.1181   0.5612   0.0233
  -6.250   0.0685   0.02573   0.02219  -0.1171   0.5552   0.0244
  -5.500   0.0665   0.01361   0.00932  -0.1089   0.5417   0.0271
  -5.250   0.0805   0.02650   0.02186  -0.1112   0.5433   0.0274
  -5.000   0.1000   0.02609   0.02140  -0.1101   0.5361   0.0281
  -4.750   0.1173   0.02504   0.02022  -0.1083   0.5288   0.0295
  -4.500   0.1328   0.02336   0.01807  -0.1047   0.5228   0.0317
  -4.250   0.1251   0.01724   0.01145  -0.0984   0.5187   0.0284
  -4.000   0.1455   0.01661   0.01066  -0.0969   0.5111   0.0292
  -3.750   0.1650   0.01539   0.00921  -0.0951   0.5047   0.0296
  -3.500   0.1858   0.01437   0.00796  -0.0935   0.4977   0.0298
  -3.250   0.2084   0.01367   0.00711  -0.0923   0.4917   0.0303
  -3.000   0.2322   0.01315   0.00646  -0.0914   0.4857   0.0307
  -2.750   0.2558   0.01293   0.00612  -0.0904   0.4796   0.0313
  -2.500   0.2804   0.01279   0.00590  -0.0896   0.4749   0.0317
  -2.250   0.3043   0.01188   0.00488  -0.0888   0.4701   0.0321
  -2.000   0.3275   0.01137   0.00430  -0.0879   0.4653   0.0326
  -1.750   0.3511   0.01106   0.00396  -0.0870   0.4613   0.0332
  -1.500   0.3751   0.01083   0.00372  -0.0861   0.4577   0.0337
  -1.250   0.3987   0.01066   0.00352  -0.0852   0.4539   0.0343
  -1.000   0.4219   0.01055   0.00338  -0.0842   0.4502   0.0352
  -0.750   0.4452   0.01045   0.00324  -0.0832   0.4466   0.0362
  -0.500   0.4693   0.01031   0.00310  -0.0824   0.4438   0.0370
  -0.250   0.4929   0.01021   0.00298  -0.0815   0.4409   0.0376
   0.000   0.5164   0.01016   0.00289  -0.0806   0.4379   0.0382
   0.250   0.5384   0.01004   0.00273  -0.0793   0.4351   0.0390
   0.500   0.5601   0.00994   0.00260  -0.0780   0.4320   0.0408
   0.750   0.5842   0.00987   0.00254  -0.0772   0.4303   0.0426
   1.000   0.6083   0.00984   0.00251  -0.0765   0.4283   0.0449
   1.250   0.6324   0.00983   0.00251  -0.0757   0.4262   0.0467
   1.500   0.6553   0.00977   0.00245  -0.0746   0.4239   0.0529
   1.750   0.6777   0.00975   0.00245  -0.0735   0.4214   0.0687
   2.000   0.6915   0.00929   0.00258  -0.0708   0.4191   0.3224
   2.250   0.6784   0.00823   0.00268  -0.0622   0.4172   0.7582
   2.500   1.0110   0.00898   0.00370  -0.1301   0.4109   1.0000
   2.750   1.0337   0.00906   0.00375  -0.1292   0.4084   1.0000
   3.000   1.0558   0.00916   0.00383  -0.1281   0.4061   1.0000
   3.250   1.0769   0.00931   0.00393  -0.1269   0.4024   1.0000
   3.500   1.0993   0.00940   0.00402  -0.1259   0.4005   1.0000
   3.750   1.1222   0.00945   0.00409  -0.1250   0.3988   1.0000
   4.000   1.1448   0.00953   0.00417  -0.1241   0.3971   1.0000
   4.250   1.1671   0.00961   0.00426  -0.1231   0.3953   1.0000
   4.500   1.1891   0.00970   0.00436  -0.1221   0.3936   1.0000
   4.750   1.2106   0.00981   0.00447  -0.1209   0.3918   1.0000
   5.000   1.2315   0.00994   0.00459  -0.1197   0.3899   1.0000
   5.250   1.2517   0.01011   0.00474  -0.1183   0.3875   1.0000
   5.500   1.2725   0.01025   0.00490  -0.1171   0.3857   1.0000
   5.750   1.2943   0.01028   0.00497  -0.1160   0.3834   1.0000
   6.000   1.3156   0.01034   0.00505  -0.1149   0.3805   1.0000
   6.250   1.3358   0.01043   0.00516  -0.1135   0.3773   1.0000
   6.500   1.3546   0.01057   0.00529  -0.1119   0.3743   1.0000
   6.750   1.3720   0.01077   0.00548  -0.1100   0.3711   1.0000
   7.000   1.3927   0.01081   0.00558  -0.1088   0.3690   1.0000
   7.250   1.4126   0.01087   0.00568  -0.1074   0.3653   1.0000
   7.500   1.4291   0.01098   0.00580  -0.1053   0.3608   1.0000
   7.750   1.4407   0.01114   0.00595  -0.1022   0.3569   1.0000
   8.000   1.4574   0.01120   0.00605  -0.1001   0.3526   1.0000
   8.250   1.4717   0.01130   0.00618  -0.0976   0.3467   1.0000
   8.500   1.4838   0.01149   0.00635  -0.0947   0.3409   1.0000
   8.750   1.4989   0.01161   0.00651  -0.0924   0.3330   1.0000
   9.000   1.5102   0.01185   0.00672  -0.0894   0.3220   1.0000
   9.250   1.5162   0.01226   0.00703  -0.0855   0.3014   1.0000
   9.500   1.5117   0.01303   0.00763  -0.0797   0.2706   1.0000
   9.750   1.5020   0.01404   0.00845  -0.0732   0.2385   1.0000
  10.000   1.4884   0.01529   0.00951  -0.0664   0.2064   1.0000
  10.250   1.4715   0.01682   0.01084  -0.0596   0.1729   1.0000
  10.500   1.4395   0.01931   0.01307  -0.0515   0.1252   1.0000
  10.750   1.4101   0.02223   0.01584  -0.0450   0.0887   1.0000
  11.000   1.3749   0.02622   0.01967  -0.0395   0.0466   1.0000
  11.250   1.3575   0.02948   0.02289  -0.0365   0.0253   1.0000
  11.500   1.3519   0.03204   0.02548  -0.0347   0.0195   1.0000
  11.750   1.3525   0.03418   0.02767  -0.0335   0.0183   1.0000
  12.000   1.3504   0.03665   0.03020  -0.0323   0.0172   1.0000
  12.250   1.3469   0.03932   0.03295  -0.0312   0.0160   1.0000
  12.500   1.3458   0.04182   0.03553  -0.0303   0.0156   1.0000
  12.750   1.3442   0.04444   0.03822  -0.0295   0.0151   1.0000
  13.000   1.3415   0.04719   0.04105  -0.0287   0.0146   1.0000
  13.250   1.3374   0.05017   0.04411  -0.0281   0.0142   1.0000
  13.500   1.3304   0.05354   0.04755  -0.0274   0.0135   1.0000
  13.750   1.3265   0.05664   0.05072  -0.0270   0.0134   1.0000
  14.000   1.3180   0.06030   0.05447  -0.0266   0.0129   1.0000
  14.250   1.3063   0.06447   0.05873  -0.0262   0.0126   1.0000
  14.500   1.3064   0.06727   0.06160  -0.0261   0.0122   1.0000
  14.750   1.3012   0.07074   0.06515  -0.0260   0.0121   1.0000
  15.000   1.2993   0.07383   0.06831  -0.0259   0.0118   1.0000
  15.250   1.2953   0.07724   0.07179  -0.0259   0.0115   1.0000
  15.500   1.2900   0.08088   0.07550  -0.0260   0.0113   1.0000
  15.750   1.2868   0.08423   0.07892  -0.0262   0.0110   1.0000
  16.000   1.2802   0.08808   0.08284  -0.0264   0.0109   1.0000
  16.250   1.2778   0.09142   0.08623  -0.0267   0.0106   1.0000
  16.500   1.2709   0.09540   0.09028  -0.0270   0.0103   1.0000
  16.750   1.2668   0.09905   0.09400  -0.0275   0.0103   1.0000
  17.000   1.2526   0.10411   0.09914  -0.0281   0.0099   1.0000
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