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GOE 63 AIRFOIL (goe63-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 63 AIRFOIL (goe63-il)
Reynolds number: 500,000
Max Cl/Cd: 102.59 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe63-il-500000-n5.txt
Download as CSV file: xf-goe63-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 63 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.1749   0.09212   0.08896  -0.0351   0.7492   0.0200
  -7.500  -0.1652   0.08951   0.08631  -0.0367   0.7404   0.0205
  -7.250  -0.1560   0.08689   0.08367  -0.0386   0.7325   0.0211
  -7.000  -0.1420   0.08392   0.08066  -0.0423   0.7246   0.0213
  -6.750  -0.1255   0.08083   0.07754  -0.0467   0.7180   0.0214
  -6.500  -0.1054   0.07757   0.07423  -0.0523   0.7111   0.0215
  -6.250  -0.0829   0.07419   0.07078  -0.0584   0.7046   0.0215
  -6.000  -0.0617   0.07086   0.06742  -0.0624   0.6985   0.0215
  -5.750  -0.0464   0.06806   0.06460  -0.0630   0.6922   0.0217
  -5.500  -0.0274   0.06546   0.06195  -0.0650   0.6867   0.0218
  -5.250  -0.0055   0.06287   0.05933  -0.0678   0.6813   0.0220
  -5.000   0.0186   0.06028   0.05669  -0.0712   0.6748   0.0223
  -4.750   0.0445   0.05766   0.05400  -0.0748   0.6683   0.0228
  -4.500   0.0725   0.05494   0.05123  -0.0787   0.6618   0.0234
  -4.250   0.1094   0.05181   0.04798  -0.0848   0.6557   0.0247
  -4.000   0.1499   0.04844   0.04445  -0.0915   0.6503   0.0249
  -3.750   0.1859   0.04529   0.04119  -0.0963   0.6448   0.0249
  -3.500   0.2199   0.04238   0.03816  -0.1000   0.6394   0.0249
  -3.000   0.2733   0.03776   0.03341  -0.1037   0.6287   0.0253
  -2.750   0.3018   0.03593   0.03152  -0.1054   0.6230   0.0256
  -2.500   0.3322   0.03415   0.02963  -0.1074   0.6173   0.0260
  -2.250   0.3642   0.03240   0.02780  -0.1094   0.6114   0.0270
  -2.000   0.4071   0.02994   0.02509  -0.1126   0.6053   0.0287
  -1.750   0.4425   0.02779   0.02273  -0.1146   0.6004   0.0288
  -1.500   0.4768   0.02572   0.02048  -0.1162   0.5962   0.0289
  -1.250   0.5097   0.02386   0.01846  -0.1176   0.5915   0.0289
  -1.000   0.5417   0.02219   0.01663  -0.1187   0.5861   0.0289
  -0.750   0.5688   0.02120   0.01563  -0.1198   0.5806   0.0280
  -0.500   0.6014   0.01973   0.01400  -0.1208   0.5747   0.0272
  -0.250   0.6343   0.01834   0.01241  -0.1216   0.5689   0.0278
   0.000   0.6666   0.01698   0.01084  -0.1223   0.5633   0.0269
   0.250   0.7002   0.01528   0.00885  -0.1230   0.5562   0.0262
   0.500   0.7317   0.01403   0.00733  -0.1234   0.5484   0.0263
   0.750   0.7623   0.01313   0.00624  -0.1237   0.5401   0.0267
   1.000   0.7919   0.01250   0.00542  -0.1239   0.5309   0.0271
   1.250   0.8212   0.01205   0.00484  -0.1240   0.5191   0.0278
   1.500   0.8498   0.01181   0.00444  -0.1240   0.5044   0.0287
   1.750   0.8780   0.01165   0.00414  -0.1240   0.4845   0.0289
   2.000   0.9057   0.01149   0.00385  -0.1240   0.4575   0.0294
   2.250   0.9329   0.01155   0.00377  -0.1239   0.4271   0.0299
   2.500   0.9598   0.01170   0.00377  -0.1238   0.3986   0.0306
   2.750   0.9868   0.01185   0.00381  -0.1237   0.3753   0.0314
   3.000   1.0139   0.01201   0.00387  -0.1236   0.3566   0.0323
   3.250   1.0411   0.01217   0.00396  -0.1235   0.3424   0.0336
   3.500   1.0683   0.01231   0.00406  -0.1235   0.3299   0.0353
   3.750   1.0954   0.01247   0.00418  -0.1234   0.3193   0.0368
   4.000   1.1226   0.01262   0.00430  -0.1233   0.3107   0.0386
   4.250   1.1496   0.01279   0.00445  -0.1232   0.3021   0.0418
   4.500   1.1767   0.01294   0.00461  -0.1231   0.2950   0.0510
   4.750   1.2038   0.01307   0.00483  -0.1230   0.2878   0.1032
   5.250   1.2504   0.01220   0.00534  -0.1215   0.2740   1.0000
   5.750   1.3029   0.01270   0.00577  -0.1211   0.2604   1.0000
   6.000   1.3287   0.01299   0.00600  -0.1208   0.2527   1.0000
   6.250   1.3545   0.01325   0.00624  -0.1205   0.2451   1.0000
   6.500   1.3797   0.01357   0.00652  -0.1202   0.2360   1.0000
   6.750   1.4051   0.01386   0.00678  -0.1198   0.2282   1.0000
   7.000   1.4296   0.01421   0.00709  -0.1194   0.2196   1.0000
   7.250   1.4544   0.01453   0.00739  -0.1190   0.2115   1.0000
   7.500   1.4782   0.01491   0.00774  -0.1185   0.2029   1.0000
   7.750   1.5020   0.01529   0.00809  -0.1179   0.1941   1.0000
   8.000   1.5250   0.01571   0.00849  -0.1173   0.1853   1.0000
   8.250   1.5466   0.01623   0.00894  -0.1165   0.1745   1.0000
   8.500   1.5686   0.01670   0.00937  -0.1157   0.1650   1.0000
   8.750   1.5898   0.01720   0.00986  -0.1148   0.1574   1.0000
   9.000   1.6108   0.01768   0.01033  -0.1139   0.1506   1.0000
   9.250   1.6308   0.01822   0.01085  -0.1128   0.1441   1.0000
   9.500   1.6505   0.01873   0.01137  -0.1117   0.1375   1.0000
   9.750   1.6685   0.01934   0.01196  -0.1104   0.1318   1.0000
  10.000   1.6871   0.01984   0.01250  -0.1091   0.1269   1.0000
  10.250   1.7030   0.02048   0.01313  -0.1075   0.1212   1.0000
  10.500   1.7179   0.02111   0.01378  -0.1057   0.1166   1.0000
  10.750   1.7307   0.02175   0.01446  -0.1035   0.1126   1.0000
  11.000   1.7421   0.02253   0.01526  -0.1012   0.1085   1.0000
  11.250   1.7536   0.02337   0.01614  -0.0992   0.1046   1.0000
  11.500   1.7652   0.02426   0.01706  -0.0973   0.0997   1.0000
  11.750   1.7744   0.02537   0.01818  -0.0953   0.0949   1.0000
  12.000   1.7853   0.02643   0.01929  -0.0937   0.0909   1.0000
  12.250   1.7942   0.02770   0.02060  -0.0921   0.0857   1.0000
  12.500   1.8022   0.02913   0.02205  -0.0905   0.0808   1.0000
  12.750   1.8086   0.03076   0.02370  -0.0891   0.0742   1.0000
  13.000   1.8123   0.03273   0.02567  -0.0876   0.0655   1.0000
  13.250   1.8089   0.03544   0.02832  -0.0860   0.0522   1.0000
  13.500   1.7868   0.04016   0.03289  -0.0839   0.0284   1.0000
  13.750   1.7760   0.04393   0.03668  -0.0825   0.0206   1.0000
  14.000   1.7724   0.04703   0.03985  -0.0816   0.0182   1.0000
  14.250   1.7704   0.04998   0.04290  -0.0809   0.0170   1.0000
  14.500   1.7682   0.05303   0.04604  -0.0803   0.0161   1.0000
  14.750   1.7648   0.05628   0.04940  -0.0798   0.0154   1.0000
  15.000   1.7600   0.05978   0.05301  -0.0795   0.0148   1.0000
  15.250   1.7556   0.06334   0.05669  -0.0793   0.0144   1.0000
  15.500   1.7519   0.06692   0.06038  -0.0793   0.0140   1.0000
  15.750   1.7469   0.07076   0.06435  -0.0794   0.0137   1.0000
  16.000   1.7405   0.07487   0.06857  -0.0797   0.0134   1.0000
  16.250   1.7326   0.07930   0.07314  -0.0802   0.0131   1.0000
  16.500   1.7233   0.08406   0.07802  -0.0810   0.0129   1.0000
  16.750   1.7125   0.08914   0.08323  -0.0819   0.0127   1.0000
  17.000   1.7002   0.09455   0.08877  -0.0831   0.0125   1.0000
  17.250   1.6868   0.10028   0.09463  -0.0846   0.0123   1.0000
  17.500   1.6721   0.10635   0.10084  -0.0863   0.0122   1.0000
  17.750   1.6562   0.11270   0.10733  -0.0883   0.0120   1.0000
  18.000   1.6396   0.11931   0.11408  -0.0906   0.0119   1.0000
  18.250   1.6227   0.12610   0.12101  -0.0932   0.0118   1.0000
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