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GOE 602 MOD. AIRFOIL (goe602m-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 602 MOD. AIRFOIL (goe602m-il)
Reynolds number: 200,000
Max Cl/Cd: 76.24 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe602m-il-200000-n5.txt
Download as CSV file: xf-goe602m-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 602 MOD. 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3829   0.08870   0.08537  -0.0370   1.0000   0.0142
  -8.500  -0.3927   0.08578   0.08252  -0.0361   1.0000   0.0143
  -8.250  -0.4060   0.08314   0.07995  -0.0346   1.0000   0.0142
  -8.000  -0.4106   0.07888   0.07575  -0.0370   0.9973   0.0144
  -7.750  -0.4025   0.07100   0.06789  -0.0469   0.9895   0.0150
  -7.500  -0.3889   0.06058   0.05745  -0.0613   0.9812   0.0151
  -7.250  -0.3791   0.04113   0.03743  -0.0826   0.9704   0.0151
  -7.000  -0.3586   0.03126   0.02654  -0.0904   0.9653   0.0157
  -6.750  -0.3406   0.02684   0.02148  -0.0915   0.9584   0.0165
  -6.500  -0.3112   0.02498   0.01937  -0.0933   0.9551   0.0175
  -6.250  -0.2780   0.02400   0.01819  -0.0952   0.9529   0.0193
  -6.000  -0.2538   0.02263   0.01650  -0.0950   0.9469   0.0217
  -5.750  -0.2235   0.02089   0.01429  -0.0959   0.9432   0.0238
  -5.500  -0.1913   0.01926   0.01239  -0.0973   0.9406   0.0265
  -5.250  -0.1565   0.01842   0.01143  -0.0991   0.9386   0.0297
  -5.000  -0.1316   0.01761   0.01044  -0.0985   0.9321   0.0325
  -4.750  -0.0985   0.01707   0.00970  -0.0996   0.9284   0.0355
  -4.500  -0.0657   0.01574   0.00826  -0.1009   0.9255   0.0386
  -4.250  -0.0377   0.01518   0.00766  -0.1010   0.9197   0.0420
  -4.000  -0.0071   0.01459   0.00696  -0.1015   0.9144   0.0442
  -3.750   0.0273   0.01400   0.00627  -0.1028   0.9107   0.0459
  -3.500   0.0540   0.01365   0.00581  -0.1025   0.9030   0.0480
  -3.250   0.0863   0.01309   0.00519  -0.1034   0.8976   0.0510
  -3.000   0.1149   0.01272   0.00476  -0.1035   0.8902   0.0541
  -2.750   0.1459   0.01239   0.00435  -0.1039   0.8836   0.0596
  -2.500   0.1742   0.01202   0.00406  -0.1040   0.8757   0.0809
  -2.250   0.2044   0.01164   0.00376  -0.1044   0.8686   0.1233
  -2.000   0.2305   0.01116   0.00357  -0.1043   0.8593   0.1993
  -1.750   0.2600   0.01086   0.00346  -0.1046   0.8514   0.2843
  -1.500   0.2875   0.01068   0.00334  -0.1045   0.8415   0.3237
  -1.250   0.3145   0.01046   0.00323  -0.1042   0.8311   0.3658
  -1.000   0.3411   0.01015   0.00320  -0.1040   0.8208   0.4443
  -0.750   0.3684   0.00994   0.00315  -0.1037   0.8098   0.5152
  -0.500   0.3951   0.00981   0.00307  -0.1032   0.7976   0.5623
  -0.250   0.4214   0.00966   0.00299  -0.1027   0.7846   0.6042
   0.000   0.4468   0.00945   0.00294  -0.1020   0.7713   0.6572
   0.250   0.4712   0.00907   0.00293  -0.1007   0.7576   0.7998
   0.500   0.5249   0.00884   0.00281  -0.1059   0.7430   1.0000
   0.750   0.5514   0.00893   0.00277  -0.1055   0.7273   1.0000
   1.000   0.5777   0.00904   0.00276  -0.1050   0.7113   1.0000
   1.250   0.6036   0.00917   0.00277  -0.1045   0.6949   1.0000
   1.500   0.6290   0.00931   0.00281  -0.1039   0.6775   1.0000
   1.750   0.6542   0.00947   0.00286  -0.1032   0.6595   1.0000
   2.000   0.6790   0.00965   0.00292  -0.1025   0.6394   1.0000
   2.250   0.7031   0.00985   0.00301  -0.1016   0.6171   1.0000
   2.500   0.7272   0.01006   0.00311  -0.1008   0.5960   1.0000
   2.750   0.7512   0.01028   0.00323  -0.1000   0.5757   1.0000
   3.000   0.7754   0.01049   0.00338  -0.0992   0.5573   1.0000
   3.250   0.7997   0.01071   0.00355  -0.0984   0.5403   1.0000
   3.500   0.8237   0.01095   0.00372  -0.0977   0.5232   1.0000
   3.750   0.8473   0.01121   0.00393  -0.0968   0.5057   1.0000
   4.000   0.8707   0.01147   0.00415  -0.0960   0.4860   1.0000
   4.250   0.8940   0.01175   0.00438  -0.0951   0.4670   1.0000
   4.500   0.9172   0.01203   0.00463  -0.0942   0.4496   1.0000
   4.750   0.9401   0.01233   0.00492  -0.0933   0.4317   1.0000
   5.000   0.9610   0.01272   0.00521  -0.0920   0.4021   1.0000
   5.250   0.9802   0.01320   0.00552  -0.0905   0.3623   1.0000
   5.500   0.9976   0.01381   0.00589  -0.0887   0.3115   1.0000
   5.750   1.0131   0.01462   0.00638  -0.0867   0.2512   1.0000
   6.000   1.0290   0.01548   0.00695  -0.0849   0.1973   1.0000
   6.250   1.0398   0.01681   0.00777  -0.0825   0.1144   1.0000
   6.500   1.0534   0.01793   0.00861  -0.0804   0.0708   1.0000
   6.750   1.0654   0.01917   0.00960  -0.0779   0.0253   1.0000
   7.000   1.0820   0.01997   0.01048  -0.0760   0.0205   1.0000
   7.250   1.0975   0.02085   0.01153  -0.0740   0.0175   1.0000
   7.500   1.1142   0.02157   0.01240  -0.0722   0.0167   1.0000
   7.750   1.1286   0.02235   0.01333  -0.0699   0.0158   1.0000
   8.000   1.1412   0.02321   0.01431  -0.0675   0.0145   1.0000
   8.250   1.1523   0.02415   0.01537  -0.0650   0.0133   1.0000
   8.500   1.1612   0.02525   0.01658  -0.0623   0.0127   1.0000
   8.750   1.1679   0.02650   0.01795  -0.0594   0.0122   1.0000
   9.000   1.1725   0.02794   0.01948  -0.0564   0.0117   1.0000
   9.250   1.1747   0.02965   0.02128  -0.0533   0.0113   1.0000
   9.500   1.1769   0.03156   0.02327  -0.0505   0.0111   1.0000
   9.750   1.1802   0.03383   0.02564  -0.0479   0.0107   1.0000
  10.000   1.1909   0.03517   0.02709  -0.0462   0.0103   1.0000
  10.250   1.2013   0.03657   0.02862  -0.0446   0.0099   1.0000
  10.500   1.2110   0.03812   0.03029  -0.0430   0.0093   1.0000
  10.750   1.2208   0.03993   0.03222  -0.0414   0.0090   1.0000
  11.000   1.2309   0.04185   0.03427  -0.0400   0.0088   1.0000
  11.250   1.2401   0.04393   0.03648  -0.0385   0.0085   1.0000
  11.500   1.2481   0.04613   0.03885  -0.0372   0.0083   1.0000
  11.750   1.2545   0.04850   0.04139  -0.0358   0.0082   1.0000
  12.000   1.2587   0.05104   0.04411  -0.0346   0.0081   1.0000
  12.250   1.2609   0.05379   0.04706  -0.0334   0.0080   1.0000
  12.500   1.2609   0.05675   0.05022  -0.0324   0.0079   1.0000
  12.750   1.2586   0.05999   0.05367  -0.0316   0.0078   1.0000
  13.000   1.2541   0.06350   0.05739  -0.0310   0.0078   1.0000
  13.250   1.2476   0.06730   0.06139  -0.0309   0.0077   1.0000
  13.500   1.2389   0.07151   0.06588  -0.0311   0.0077   1.0000
  13.750   1.2287   0.07603   0.07061  -0.0318   0.0077   1.0000
  14.000   1.2182   0.08072   0.07549  -0.0330   0.0076   1.0000
  14.250   1.2063   0.08584   0.08080  -0.0347   0.0076   1.0000
  14.500   1.1936   0.09139   0.08654  -0.0370   0.0075   1.0000
  14.750   1.1795   0.09747   0.09282  -0.0398   0.0075   1.0000
  15.000   1.1645   0.10415   0.09970  -0.0432   0.0076   1.0000
  15.250   1.1417   0.11298   0.10882  -0.0485   0.0078   1.0000
  15.500   1.1358   0.11830   0.11420  -0.0515   0.0075   1.0000
  15.750   1.1055   0.13033   0.12651  -0.0594   0.0079   1.0000
  16.000   1.0828   0.14147   0.13785  -0.0668   0.0081   1.0000
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