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GOE 63 AIRFOIL (goe63-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 63 AIRFOIL (goe63-il)
Reynolds number: 1,000,000
Max Cl/Cd: 128.44 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe63-il-1000000.txt
Download as CSV file: xf-goe63-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2203   0.10242   0.10023  -0.0277   0.8205   0.0167
  -8.500  -0.2114   0.09977   0.09751  -0.0290   0.8056   0.0172
  -8.250  -0.2021   0.09695   0.09465  -0.0307   0.7930   0.0178
  -8.000  -0.1933   0.09407   0.09172  -0.0332   0.7818   0.0181
  -7.750  -0.1855   0.09132   0.08892  -0.0358   0.7707   0.0181
  -7.500  -0.1762   0.08851   0.08609  -0.0391   0.7608   0.0181
  -7.250  -0.1612   0.08530   0.08282  -0.0440   0.7512   0.0182
  -7.000  -0.1464   0.08173   0.07923  -0.0472   0.7424   0.0182
  -6.750  -0.1341   0.07873   0.07618  -0.0473   0.7340   0.0183
  -6.500  -0.1183   0.07601   0.07344  -0.0493   0.7261   0.0184
  -6.250  -0.1008   0.07340   0.07079  -0.0519   0.7179   0.0186
  -6.000  -0.0813   0.07079   0.06815  -0.0550   0.7100   0.0188
  -5.750  -0.0603   0.06815   0.06545  -0.0584   0.7016   0.0191
  -5.500  -0.0374   0.06533   0.06260  -0.0622   0.6941   0.0195
  -5.250  -0.0127   0.06241   0.05963  -0.0663   0.6871   0.0201
  -5.000   0.0218   0.05892   0.05605  -0.0732   0.6809   0.0211
  -4.750   0.0600   0.05528   0.05231  -0.0810   0.6749   0.0212
  -4.500   0.0943   0.05186   0.04879  -0.0866   0.6687   0.0212
  -4.250   0.1236   0.04812   0.04497  -0.0907   0.6634   0.0213
  -4.000   0.1455   0.04576   0.04259  -0.0919   0.6583   0.0215
  -3.750   0.1713   0.04363   0.04041  -0.0938   0.6528   0.0217
  -3.500   0.2000   0.04152   0.03823  -0.0963   0.6473   0.0219
  -3.250   0.2307   0.03938   0.03604  -0.0990   0.6420   0.0223
  -3.000   0.2629   0.03718   0.03375  -0.1018   0.6363   0.0229
  -2.750   0.3065   0.03440   0.03076  -0.1061   0.6311   0.0245
  -2.500   0.3456   0.03169   0.02791  -0.1093   0.6273   0.0246
  -2.250   0.3798   0.02943   0.02553  -0.1114   0.6228   0.0247
  -2.000   0.4088   0.02686   0.02286  -0.1134   0.6181   0.0250
  -1.750   0.4380   0.02551   0.02143  -0.1146   0.6134   0.0252
  -1.500   0.4687   0.02414   0.02001  -0.1159   0.6095   0.0255
  -1.250   0.5003   0.02277   0.01854  -0.1171   0.6050   0.0261
  -1.000   0.5332   0.02129   0.01692  -0.1182   0.6003   0.0273
  -0.750   0.5728   0.01846   0.01373  -0.1197   0.5957   0.0289
  -0.500   0.6025   0.01759   0.01282  -0.1205   0.5907   0.0292
  -0.250   0.6324   0.01681   0.01196  -0.1211   0.5855   0.0297
   0.000   0.6630   0.01600   0.01102  -0.1217   0.5800   0.0306
   0.250   0.6968   0.01515   0.00990  -0.1217   0.5746   0.0329
   0.500   0.7278   0.01359   0.00823  -0.1228   0.5681   0.0337
   0.750   0.7572   0.01311   0.00768  -0.1232   0.5613   0.0344
   1.000   0.7872   0.01259   0.00707  -0.1235   0.5523   0.0357
   1.500   0.8499   0.01046   0.00437  -0.1239   0.5318   0.0332
   1.750   0.8791   0.01000   0.00387  -0.1240   0.5192   0.0323
   2.000   0.9080   0.00977   0.00354  -0.1241   0.5034   0.0325
   2.250   0.9362   0.00978   0.00342  -0.1241   0.4826   0.0329
   2.500   0.9645   0.00961   0.00312  -0.1242   0.4552   0.0330
   2.750   0.9923   0.00957   0.00294  -0.1243   0.4225   0.0339
   3.000   1.0195   0.00978   0.00299  -0.1242   0.3900   0.0349
   3.250   1.0468   0.00999   0.00308  -0.1242   0.3659   0.0360
   3.500   1.0744   0.01015   0.00316  -0.1242   0.3492   0.0372
   4.000   1.1298   0.01040   0.00333  -0.1242   0.3249   0.0422
   4.250   1.1574   0.01054   0.00344  -0.1242   0.3161   0.0469
   4.500   1.1854   0.01062   0.00359  -0.1242   0.3081   0.0992
   4.750   1.2076   0.00947   0.00395  -0.1235   0.3006   1.0000
   5.000   1.2351   0.00964   0.00409  -0.1234   0.2935   1.0000
   5.250   1.2620   0.00988   0.00426  -0.1233   0.2859   1.0000
   5.500   1.2895   0.01004   0.00440  -0.1233   0.2803   1.0000
   5.750   1.3164   0.01026   0.00458  -0.1232   0.2732   1.0000
   6.000   1.3433   0.01046   0.00476  -0.1231   0.2663   1.0000
   6.250   1.3700   0.01068   0.00494  -0.1229   0.2584   1.0000
   6.500   1.3964   0.01092   0.00514  -0.1228   0.2508   1.0000
   6.750   1.4228   0.01115   0.00535  -0.1226   0.2428   1.0000
   7.000   1.4487   0.01141   0.00557  -0.1224   0.2347   1.0000
   7.250   1.4742   0.01172   0.00582  -0.1221   0.2241   1.0000
   7.500   1.4995   0.01203   0.00608  -0.1218   0.2126   1.0000
   7.750   1.5242   0.01237   0.00637  -0.1214   0.2017   1.0000
   8.000   1.5483   0.01277   0.00670  -0.1210   0.1897   1.0000
   8.250   1.5718   0.01320   0.00706  -0.1204   0.1777   1.0000
   8.500   1.5956   0.01357   0.00740  -0.1199   0.1687   1.0000
   8.750   1.6190   0.01397   0.00777  -0.1194   0.1609   1.0000
   9.000   1.6420   0.01438   0.00815  -0.1188   0.1534   1.0000
   9.250   1.6648   0.01478   0.00854  -0.1181   0.1465   1.0000
   9.500   1.6866   0.01525   0.00897  -0.1173   0.1389   1.0000
   9.750   1.7088   0.01566   0.00937  -0.1166   0.1333   1.0000
  10.000   1.7300   0.01611   0.00980  -0.1157   0.1274   1.0000
  10.250   1.7506   0.01659   0.01028  -0.1148   0.1217   1.0000
  10.500   1.7713   0.01702   0.01072  -0.1138   0.1170   1.0000
  10.750   1.7895   0.01760   0.01127  -0.1125   0.1109   1.0000
  11.000   1.8088   0.01805   0.01174  -0.1113   0.1068   1.0000
  11.250   1.8250   0.01865   0.01233  -0.1097   0.1010   1.0000
  11.500   1.8409   0.01922   0.01291  -0.1080   0.0961   1.0000
  11.750   1.8526   0.01991   0.01358  -0.1057   0.0900   1.0000
  12.000   1.8620   0.02070   0.01437  -0.1030   0.0833   1.0000
  12.250   1.8677   0.02180   0.01543  -0.1001   0.0734   1.0000
  12.500   1.8650   0.02358   0.01708  -0.0964   0.0567   1.0000
  12.750   1.8459   0.02685   0.02017  -0.0918   0.0304   1.0000
  13.000   1.8382   0.02962   0.02292  -0.0891   0.0205   1.0000
  13.250   1.8408   0.03169   0.02504  -0.0875   0.0181   1.0000
  13.500   1.8442   0.03374   0.02716  -0.0861   0.0170   1.0000
  13.750   1.8458   0.03604   0.02954  -0.0849   0.0161   1.0000
  14.000   1.8484   0.03831   0.03189  -0.0838   0.0154   1.0000
  14.250   1.8517   0.04053   0.03419  -0.0829   0.0150   1.0000
  14.500   1.8533   0.04297   0.03673  -0.0820   0.0146   1.0000
  14.750   1.8532   0.04567   0.03951  -0.0812   0.0142   1.0000
  15.000   1.8508   0.04863   0.04257  -0.0805   0.0139   1.0000
  15.250   1.8463   0.05192   0.04595  -0.0798   0.0135   1.0000
  15.500   1.8397   0.05556   0.04970  -0.0794   0.0132   1.0000
  15.750   1.8298   0.05970   0.05396  -0.0791   0.0129   1.0000
  16.000   1.8226   0.06365   0.05802  -0.0790   0.0127   1.0000
  16.250   1.8184   0.06731   0.06178  -0.0790   0.0125   1.0000
  16.500   1.8120   0.07136   0.06594  -0.0793   0.0124   1.0000
  16.750   1.8041   0.07567   0.07036  -0.0796   0.0122   1.0000
  17.000   1.7945   0.08034   0.07514  -0.0802   0.0120   1.0000
  17.250   1.7838   0.08530   0.08022  -0.0810   0.0118   1.0000
  17.500   1.7713   0.09062   0.08565  -0.0821   0.0117   1.0000
  17.750   1.7571   0.09629   0.09144  -0.0834   0.0116   1.0000
  18.000   1.7418   0.10230   0.09758  -0.0849   0.0115   1.0000
  18.250   1.7258   0.10853   0.10393  -0.0868   0.0114   1.0000
  18.500   1.7082   0.11511   0.11065  -0.0889   0.0113   1.0000
  18.750   1.6908   0.12175   0.11741  -0.0912   0.0113   1.0000
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