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GOE 450 AIRFOIL (goe450-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 450 AIRFOIL (goe450-il)
Reynolds number: 200,000
Max Cl/Cd: 88.17 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe450-il-200000.txt
Download as CSV file: xf-goe450-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 450 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3432   0.10215   0.09881  -0.0282   1.0000   0.0381
  -8.000  -0.3590   0.10136   0.09810  -0.0259   1.0000   0.0386
  -7.750  -0.3792   0.10095   0.09778  -0.0231   1.0000   0.0389
  -7.500  -0.3539   0.09602   0.09283  -0.0404   0.9920   0.0395
  -7.250  -0.3431   0.09044   0.08726  -0.0396   0.9893   0.0403
  -7.000  -0.3249   0.08717   0.08398  -0.0387   0.9869   0.0417
  -6.750  -0.2981   0.08306   0.07984  -0.0446   0.9836   0.0437
  -6.500  -0.2758   0.07891   0.07566  -0.0512   0.9763   0.0460
  -6.250  -0.2192   0.07084   0.06735  -0.0770   0.9674   0.0495
  -6.000  -0.2096   0.06717   0.06376  -0.0743   0.9630   0.0505
  -5.750  -0.1853   0.06428   0.06084  -0.0758   0.9597   0.0524
  -5.500  -0.1250   0.05918   0.05527  -0.0935   0.9523   0.0605
  -5.250  -0.1078   0.05373   0.04992  -0.0950   0.9475   0.0619
  -5.000  -0.0801   0.05109   0.04731  -0.0968   0.9447   0.0640
  -4.750  -0.0385   0.04759   0.04365  -0.1031   0.9425   0.0698
  -4.500  -0.0059   0.04305   0.03880  -0.1084   0.9338   0.0757
  -4.250   0.0274   0.04085   0.03660  -0.1111   0.9307   0.0804
  -4.000   0.0745   0.03676   0.03210  -0.1178   0.9284   0.0902
  -3.750   0.1017   0.03482   0.03015  -0.1189   0.9222   0.0943
  -3.500   0.1383   0.03210   0.02707  -0.1220   0.9168   0.1054
  -3.250   0.1776   0.03021   0.02487  -0.1251   0.9137   0.1192
  -3.000   0.2035   0.02832   0.02308  -0.1255   0.9070   0.1249
  -2.750   0.2358   0.02655   0.02113  -0.1269   0.9011   0.1386
  -2.500   0.2711   0.02490   0.01935  -0.1287   0.8976   0.1547
  -2.250   0.3130   0.01942   0.01243  -0.1279   0.8898   0.0681
  -2.000   0.3462   0.01809   0.01085  -0.1284   0.8844   0.0676
  -1.750   0.3752   0.01702   0.00956  -0.1281   0.8766   0.0665
  -1.500   0.4057   0.01599   0.00837  -0.1280   0.8696   0.0654
  -1.250   0.4337   0.01524   0.00755  -0.1275   0.8612   0.0655
  -1.000   0.4631   0.01453   0.00680  -0.1273   0.8538   0.0664
  -0.750   0.4898   0.01403   0.00629  -0.1267   0.8440   0.0680
  -0.500   0.5196   0.01353   0.00575  -0.1266   0.8370   0.0713
  -0.250   0.5455   0.01316   0.00540  -0.1260   0.8261   0.0756
   0.000   0.5732   0.01282   0.00506  -0.1257   0.8170   0.0818
   0.250   0.6017   0.01247   0.00471  -0.1255   0.8082   0.0973
   0.500   0.6268   0.01019   0.00470  -0.1249   0.7986   1.0000
   0.750   0.6550   0.01020   0.00451  -0.1246   0.7898   1.0000
   1.000   0.6821   0.01026   0.00444  -0.1242   0.7795   1.0000
   1.250   0.7089   0.01034   0.00441  -0.1238   0.7691   1.0000
   1.500   0.7367   0.01040   0.00436  -0.1236   0.7598   1.0000
   1.750   0.7636   0.01050   0.00438  -0.1232   0.7493   1.0000
   2.000   0.7902   0.01062   0.00443  -0.1228   0.7386   1.0000
   2.250   0.8175   0.01073   0.00446  -0.1226   0.7286   1.0000
   2.500   0.8444   0.01085   0.00451  -0.1222   0.7178   1.0000
   2.750   0.8705   0.01099   0.00461  -0.1218   0.7059   1.0000
   3.000   0.8968   0.01114   0.00472  -0.1213   0.6938   1.0000
   3.250   0.9231   0.01129   0.00482  -0.1209   0.6817   1.0000
   3.500   0.9495   0.01145   0.00492  -0.1204   0.6695   1.0000
   3.750   0.9755   0.01163   0.00503  -0.1199   0.6562   1.0000
   4.000   1.0007   0.01180   0.00520  -0.1193   0.6418   1.0000
   4.250   1.0256   0.01198   0.00533  -0.1186   0.6262   1.0000
   4.500   1.0502   0.01217   0.00549  -0.1178   0.6099   1.0000
   4.750   1.0745   0.01237   0.00569  -0.1170   0.5934   1.0000
   5.000   1.0984   0.01257   0.00589  -0.1162   0.5760   1.0000
   5.250   1.1215   0.01276   0.00607  -0.1152   0.5556   1.0000
   5.500   1.1446   0.01299   0.00627  -0.1142   0.5360   1.0000
   5.750   1.1674   0.01324   0.00652  -0.1132   0.5160   1.0000
   6.000   1.1898   0.01352   0.00679  -0.1122   0.4948   1.0000
   6.250   1.2113   0.01386   0.00708  -0.1110   0.4722   1.0000
   6.500   1.2313   0.01426   0.00741  -0.1096   0.4452   1.0000
   6.750   1.2515   0.01469   0.00782  -0.1082   0.4192   1.0000
   7.000   1.2693   0.01524   0.00827  -0.1065   0.3870   1.0000
   7.250   1.2842   0.01595   0.00881  -0.1043   0.3432   1.0000
   7.500   1.2942   0.01697   0.00953  -0.1014   0.2778   1.0000
   7.750   1.2891   0.01916   0.01090  -0.0966   0.1606   1.0000
   8.000   1.2838   0.02138   0.01252  -0.0917   0.0836   1.0000
   8.250   1.2889   0.02275   0.01385  -0.0882   0.0683   1.0000
   8.500   1.2951   0.02406   0.01517  -0.0851   0.0611   1.0000
   8.750   1.3050   0.02515   0.01635  -0.0825   0.0565   1.0000
   9.000   1.3131   0.02638   0.01762  -0.0800   0.0525   1.0000
   9.250   1.3151   0.02809   0.01935  -0.0768   0.0497   1.0000
   9.500   1.3228   0.02946   0.02086  -0.0744   0.0477   1.0000
   9.750   1.3294   0.03098   0.02246  -0.0720   0.0456   1.0000
  10.000   1.3355   0.03259   0.02412  -0.0697   0.0436   1.0000
  10.250   1.3389   0.03459   0.02612  -0.0672   0.0416   1.0000
  10.500   1.3461   0.03656   0.02813  -0.0650   0.0401   1.0000
  10.750   1.3583   0.03810   0.02979  -0.0632   0.0389   1.0000
  11.000   1.3718   0.03970   0.03150  -0.0616   0.0376   1.0000
  11.250   1.3850   0.04132   0.03321  -0.0600   0.0360   1.0000
  11.500   1.3985   0.04303   0.03496  -0.0587   0.0344   1.0000
  11.750   1.4437   0.04661   0.03855  -0.0597   0.0323   1.0000
  12.000   1.4506   0.04851   0.04070  -0.0576   0.0319   1.0000
  12.250   1.4576   0.05078   0.04325  -0.0556   0.0314   1.0000
  12.500   1.4610   0.05321   0.04596  -0.0535   0.0309   1.0000
  12.750   1.4612   0.05583   0.04886  -0.0513   0.0303   1.0000
  13.000   1.4591   0.05869   0.05197  -0.0493   0.0297   1.0000
  13.250   1.4545   0.06182   0.05537  -0.0473   0.0292   1.0000
  13.500   1.4470   0.06545   0.05928  -0.0455   0.0291   1.0000
  13.750   1.4357   0.06952   0.06363  -0.0440   0.0291   1.0000
  14.000   1.4214   0.07398   0.06837  -0.0428   0.0292   1.0000
  14.250   1.4046   0.07885   0.07352  -0.0421   0.0294   1.0000
  14.500   1.3855   0.08412   0.07905  -0.0420   0.0296   1.0000
  14.750   1.3647   0.08982   0.08500  -0.0426   0.0299   1.0000
  15.000   1.3428   0.09591   0.09132  -0.0439   0.0302   1.0000
  15.250   1.3204   0.10249   0.09810  -0.0460   0.0305   1.0000
  15.500   1.2977   0.10960   0.10541  -0.0490   0.0309   1.0000
  15.750   1.2754   0.11719   0.11318  -0.0526   0.0312   1.0000
  16.000   1.2541   0.12528   0.12141  -0.0566   0.0317   1.0000
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