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GOE 562 AIRFOIL (goe562-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 562 AIRFOIL (goe562-il)
Reynolds number: 1,000,000
Max Cl/Cd: 126.28 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe562-il-1000000.txt
Download as CSV file: xf-goe562-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 562 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250   0.0582   0.08527   0.08280  -0.1115   0.7833   0.0177
 -11.000   0.0657   0.08160   0.07896  -0.1137   0.7484   0.0177
 -10.750   0.0715   0.07805   0.07528  -0.1155   0.7216   0.0178
 -10.500   0.0721   0.07369   0.07083  -0.1166   0.7013   0.0179
 -10.250   0.0828   0.07138   0.06843  -0.1171   0.6806   0.0181
 -10.000   0.0911   0.06894   0.06592  -0.1178   0.6660   0.0183
  -9.750   0.0054   0.07803   0.07514  -0.1165   0.7128   0.0179
  -9.500   0.0211   0.07693   0.07391  -0.1167   0.6871   0.0182
  -9.250   0.0322   0.07458   0.07148  -0.1185   0.6701   0.0184
  -9.000   0.0421   0.07173   0.06856  -0.1211   0.6566   0.0186
  -8.750   0.0551   0.06962   0.06640  -0.1232   0.6450   0.0193
  -8.250   0.0442   0.05939   0.05615  -0.1339   0.6298   0.0215
  -8.000   0.0323   0.05527   0.05200  -0.1343   0.6232   0.0216
  -7.750   0.0408   0.03471   0.03150  -0.1304   0.6059   0.0218
  -7.500   0.0365   0.03211   0.02887  -0.1290   0.6006   0.0221
  -7.250   0.0371   0.02971   0.02639  -0.1278   0.5953   0.0222
  -7.000   0.0511   0.02929   0.02595  -0.1266   0.5894   0.0226
  -6.750   0.0536   0.02672   0.02331  -0.1253   0.5847   0.0229
  -6.500   0.0596   0.02467   0.02117  -0.1238   0.5798   0.0235
  -6.250   0.0483   0.03460   0.03057  -0.1247   0.5849   0.0261
  -6.000   0.0488   0.03142   0.02714  -0.1208   0.5803   0.0261
  -5.250   0.0432   0.02121   0.01596  -0.1059   0.5679   0.0264
  -5.000   0.0493   0.01879   0.01322  -0.1018   0.5632   0.0266
  -4.750   0.1009   0.02337   0.01845  -0.1077   0.5561   0.0295
  -4.500   0.1199   0.02306   0.01778  -0.1047   0.5512   0.0316
  -4.250   0.1206   0.01925   0.01377  -0.1001   0.5473   0.0298
  -4.000   0.1315   0.01714   0.01134  -0.0964   0.5432   0.0292
  -3.750   0.1497   0.01607   0.01007  -0.0943   0.5380   0.0298
  -3.500   0.1686   0.01499   0.00879  -0.0922   0.5330   0.0300
  -3.250   0.1889   0.01413   0.00774  -0.0904   0.5269   0.0303
  -3.000   0.2113   0.01343   0.00690  -0.0892   0.5221   0.0306
  -2.750   0.2338   0.01303   0.00639  -0.0879   0.5166   0.0310
  -2.500   0.2567   0.01317   0.00644  -0.0867   0.5120   0.0316
  -2.250   0.2800   0.01212   0.00528  -0.0857   0.5076   0.0320
  -2.000   0.3027   0.01145   0.00455  -0.0846   0.5021   0.0324
  -1.750   0.3246   0.01108   0.00413  -0.0833   0.4972   0.0328
  -1.500   0.3476   0.01078   0.00383  -0.0822   0.4933   0.0333
  -1.250   0.3698   0.01055   0.00357  -0.0809   0.4889   0.0339
  -1.000   0.3914   0.01038   0.00337  -0.0795   0.4843   0.0343
  -0.750   0.4139   0.01027   0.00324  -0.0783   0.4802   0.0354
  -0.500   0.4363   0.01010   0.00306  -0.0771   0.4760   0.0360
  -0.250   0.4583   0.01000   0.00293  -0.0758   0.4712   0.0368
   0.000   0.4795   0.00992   0.00280  -0.0743   0.4659   0.0376
   0.250   0.5029   0.00984   0.00272  -0.0734   0.4623   0.0382
   0.500   0.5246   0.00972   0.00256  -0.0720   0.4573   0.0388
   0.750   0.5451   0.00959   0.00238  -0.0704   0.4524   0.0405
   1.000   0.5681   0.00954   0.00233  -0.0694   0.4487   0.0419
   1.250   0.5915   0.00950   0.00230  -0.0684   0.4448   0.0443
   1.500   0.6143   0.00951   0.00228  -0.0673   0.4404   0.0464
   1.750   0.6359   0.00951   0.00224  -0.0660   0.4363   0.0503
   2.000   0.6592   0.00949   0.00224  -0.0651   0.4331   0.0563
   2.250   0.6797   0.00923   0.00230  -0.0636   0.4297   0.1939
   2.500   1.0062   0.00869   0.00348  -0.1322   0.4157   1.0000
   2.750   1.0285   0.00877   0.00354  -0.1311   0.4118   1.0000
   3.000   1.0500   0.00888   0.00361  -0.1299   0.4074   1.0000
   3.250   1.0719   0.00897   0.00368  -0.1288   0.4037   1.0000
   3.500   1.0945   0.00905   0.00375  -0.1278   0.3998   1.0000
   3.750   1.1162   0.00914   0.00383  -0.1266   0.3955   1.0000
   4.000   1.1369   0.00928   0.00393  -0.1253   0.3908   1.0000
   4.250   1.1590   0.00936   0.00402  -0.1242   0.3869   1.0000
   4.500   1.1806   0.00946   0.00412  -0.1230   0.3821   1.0000
   4.750   1.2008   0.00961   0.00424  -0.1216   0.3769   1.0000
   5.000   1.2218   0.00972   0.00435  -0.1203   0.3723   1.0000
   5.250   1.2426   0.00984   0.00447  -0.1190   0.3660   1.0000
   5.500   1.2615   0.01002   0.00461  -0.1173   0.3568   1.0000
   5.750   1.2795   0.01021   0.00475  -0.1155   0.3471   1.0000
   6.000   1.2966   0.01038   0.00490  -0.1134   0.3372   1.0000
   6.250   1.3109   0.01062   0.00509  -0.1108   0.3239   1.0000
   6.500   1.3233   0.01093   0.00531  -0.1078   0.3072   1.0000
   6.750   1.3352   0.01126   0.00556  -0.1048   0.2918   1.0000
   7.000   1.3456   0.01166   0.00587  -0.1016   0.2752   1.0000
   7.250   1.3589   0.01196   0.00614  -0.0989   0.2656   1.0000
   7.500   1.3709   0.01231   0.00644  -0.0959   0.2564   1.0000
   7.750   1.3840   0.01263   0.00674  -0.0933   0.2482   1.0000
   8.000   1.3977   0.01295   0.00704  -0.0908   0.2420   1.0000
   8.250   1.4120   0.01324   0.00734  -0.0885   0.2363   1.0000
   8.500   1.4234   0.01364   0.00772  -0.0856   0.2296   1.0000
   8.750   1.4383   0.01394   0.00802  -0.0835   0.2246   1.0000
   9.000   1.4503   0.01434   0.00841  -0.0808   0.2186   1.0000
   9.250   1.4617   0.01476   0.00882  -0.0781   0.2103   1.0000
   9.500   1.4717   0.01527   0.00931  -0.0753   0.2027   1.0000
   9.750   1.4803   0.01583   0.00983  -0.0723   0.1907   1.0000
  10.000   1.4764   0.01694   0.01077  -0.0674   0.1620   1.0000
  10.250   1.4445   0.01942   0.01299  -0.0588   0.1092   1.0000
  10.500   1.4170   0.02221   0.01563  -0.0522   0.0681   1.0000
  10.750   1.4051   0.02451   0.01786  -0.0482   0.0466   1.0000
  11.250   1.3916   0.02917   0.02245  -0.0430   0.0184   1.0000
  11.500   1.3923   0.03117   0.02450  -0.0414   0.0162   1.0000
  11.750   1.3955   0.03305   0.02645  -0.0402   0.0155   1.0000
  12.000   1.3967   0.03519   0.02868  -0.0390   0.0147   1.0000
  12.250   1.3975   0.03742   0.03097  -0.0380   0.0143   1.0000
  12.500   1.3954   0.04001   0.03364  -0.0369   0.0137   1.0000
  12.750   1.3897   0.04302   0.03674  -0.0359   0.0130   1.0000
  13.000   1.3874   0.04572   0.03953  -0.0351   0.0126   1.0000
  13.250   1.3855   0.04845   0.04233  -0.0344   0.0123   1.0000
  13.500   1.3824   0.05136   0.04532  -0.0337   0.0118   1.0000
  13.750   1.3773   0.05454   0.04859  -0.0332   0.0117   1.0000
  14.000   1.3721   0.05779   0.05192  -0.0327   0.0114   1.0000
  14.250   1.3675   0.06103   0.05524  -0.0324   0.0113   1.0000
  14.500   1.3597   0.06474   0.05904  -0.0321   0.0109   1.0000
  14.750   1.3510   0.06863   0.06302  -0.0319   0.0108   1.0000
  15.000   1.3418   0.07264   0.06710  -0.0318   0.0105   1.0000
  15.250   1.3322   0.07680   0.07135  -0.0319   0.0104   1.0000
  15.500   1.3138   0.08222   0.07689  -0.0321   0.0101   1.0000
  15.750   1.3030   0.08666   0.08143  -0.0324   0.0100   1.0000
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