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GOE 195 AIRFOIL (goe195-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 195 AIRFOIL (goe195-il)
Reynolds number: 200,000
Max Cl/Cd: 85.96 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe195-il-200000.txt
Download as CSV file: xf-goe195-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 195 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  -0.3351   0.09846   0.09491  -0.0327   1.0000   0.0509
  -8.000  -0.3554   0.09784   0.09440  -0.0315   1.0000   0.0514
  -7.750  -0.3694   0.09637   0.09302  -0.0317   1.0000   0.0516
  -7.500  -0.3730   0.09220   0.08891  -0.0298   1.0000   0.0523
  -7.250  -0.3669   0.08977   0.08650  -0.0258   1.0000   0.0532
  -7.000  -0.3654   0.08796   0.08472  -0.0233   1.0000   0.0542
  -6.750  -0.3673   0.08623   0.08303  -0.0215   1.0000   0.0552
  -6.500  -0.3708   0.08444   0.08130  -0.0204   1.0000   0.0565
  -6.250  -0.3638   0.08167   0.07855  -0.0229   0.9986   0.0589
  -6.000  -0.3166   0.07252   0.06933  -0.0452   0.9915   0.0642
  -5.750  -0.2958   0.07076   0.06757  -0.0434   0.9879   0.0665
  -5.500  -0.2309   0.06117   0.05779  -0.0690   0.9817   0.0766
  -5.250  -0.2123   0.05951   0.05616  -0.0665   0.9766   0.0782
  -5.000  -0.1487   0.05132   0.04769  -0.0864   0.9722   0.0904
  -4.750  -0.1269   0.05004   0.04648  -0.0848   0.9672   0.0922
  -4.500  -0.0782   0.04474   0.04097  -0.0959   0.9618   0.1054
  -4.250  -0.0475   0.04347   0.03974  -0.0965   0.9586   0.1091
  -4.000  -0.0004   0.03913   0.03519  -0.1050   0.9549   0.1220
  -3.750   0.0796   0.02172   0.01535  -0.1231   0.9538   0.0647
  -3.500   0.1174   0.02066   0.01397  -0.1248   0.9480   0.0635
  -3.250   0.1594   0.01886   0.01194  -0.1277   0.9450   0.0621
  -3.000   0.2031   0.01733   0.01018  -0.1307   0.9428   0.0614
  -2.750   0.2363   0.01636   0.00908  -0.1315   0.9352   0.0614
  -2.500   0.2743   0.01543   0.00809  -0.1332   0.9304   0.0618
  -2.250   0.3137   0.01461   0.00722  -0.1351   0.9268   0.0636
  -2.000   0.3431   0.01384   0.00650  -0.1351   0.9166   0.0656
  -1.750   0.3784   0.01320   0.00588  -0.1362   0.9103   0.0676
  -1.500   0.4084   0.01278   0.00542  -0.1361   0.8999   0.0706
  -1.250   0.4387   0.01242   0.00501  -0.1361   0.8895   0.0750
  -1.000   0.4703   0.01192   0.00454  -0.1362   0.8799   0.0890
  -0.750   0.4992   0.01131   0.00448  -0.1362   0.8673   0.2529
  -0.500   0.5270   0.01128   0.00445  -0.1356   0.8532   0.3018
  -0.250   0.5547   0.01117   0.00432  -0.1351   0.8383   0.3286
   0.000   0.5823   0.01103   0.00416  -0.1346   0.8222   0.3484
   0.250   0.6097   0.01091   0.00404  -0.1340   0.8054   0.3744
   0.500   0.6364   0.01082   0.00399  -0.1334   0.7862   0.3994
   0.750   0.6630   0.01076   0.00398  -0.1328   0.7670   0.4325
   1.000   0.6895   0.01072   0.00403  -0.1322   0.7483   0.4824
   1.250   0.7150   0.01056   0.00409  -0.1314   0.7303   0.5820
   1.500   0.7388   0.00989   0.00397  -0.1298   0.7123   1.0000
   1.750   0.7654   0.01008   0.00399  -0.1293   0.6935   1.0000
   2.000   0.7921   0.01027   0.00405  -0.1288   0.6771   1.0000
   2.250   0.8191   0.01047   0.00413  -0.1284   0.6634   1.0000
   2.500   0.8461   0.01066   0.00423  -0.1280   0.6506   1.0000
   2.750   0.8730   0.01084   0.00437  -0.1277   0.6381   1.0000
   3.000   0.8997   0.01103   0.00449  -0.1273   0.6252   1.0000
   3.250   0.9260   0.01122   0.00462  -0.1268   0.6115   1.0000
   3.500   0.9523   0.01142   0.00475  -0.1263   0.5983   1.0000
   3.750   0.9786   0.01166   0.00492  -0.1258   0.5860   1.0000
   4.250   1.0307   0.01219   0.00535  -0.1248   0.5603   1.0000
   4.500   1.0562   0.01248   0.00560  -0.1241   0.5459   1.0000
   4.750   1.0810   0.01280   0.00584  -0.1234   0.5291   1.0000
   5.000   1.1057   0.01311   0.00612  -0.1227   0.5123   1.0000
   5.250   1.1306   0.01338   0.00640  -0.1220   0.4971   1.0000
   5.500   1.1554   0.01362   0.00669  -0.1213   0.4820   1.0000
   5.750   1.1794   0.01386   0.00695  -0.1204   0.4641   1.0000
   6.000   1.2033   0.01404   0.00720  -0.1195   0.4426   1.0000
   6.250   1.2266   0.01427   0.00744  -0.1186   0.4185   1.0000
   6.500   1.2492   0.01456   0.00771  -0.1175   0.3887   1.0000
   6.750   1.2700   0.01502   0.00806  -0.1162   0.3502   1.0000
   7.000   1.2877   0.01578   0.00857  -0.1145   0.3029   1.0000
   7.250   1.3055   0.01662   0.00921  -0.1130   0.2618   1.0000
   7.500   1.3224   0.01757   0.00995  -0.1113   0.2207   1.0000
   7.750   1.3381   0.01864   0.01079  -0.1095   0.1706   1.0000
   8.000   1.3493   0.02016   0.01190  -0.1072   0.1166   1.0000
   8.250   1.3597   0.02173   0.01323  -0.1046   0.0805   1.0000
   8.500   1.3730   0.02295   0.01435  -0.1024   0.0639   1.0000
   8.750   1.3861   0.02408   0.01548  -0.1001   0.0567   1.0000
   9.000   1.3972   0.02529   0.01671  -0.0976   0.0521   1.0000
   9.250   1.4043   0.02661   0.01809  -0.0945   0.0491   1.0000
   9.500   1.4127   0.02781   0.01938  -0.0917   0.0464   1.0000
   9.750   1.4188   0.02922   0.02085  -0.0887   0.0442   1.0000
  10.000   1.4209   0.03106   0.02270  -0.0854   0.0425   1.0000
  10.250   1.4249   0.03300   0.02471  -0.0825   0.0411   1.0000
  10.500   1.4340   0.03453   0.02637  -0.0802   0.0399   1.0000
  10.750   1.4427   0.03615   0.02811  -0.0780   0.0383   1.0000
  11.000   1.4512   0.03787   0.02989  -0.0760   0.0367   1.0000
  11.250   1.4608   0.03974   0.03180  -0.0741   0.0355   1.0000
  11.500   1.4776   0.04216   0.03421  -0.0727   0.0342   1.0000
  11.750   1.4956   0.04487   0.03709  -0.0715   0.0332   1.0000
  12.000   1.5018   0.04678   0.03925  -0.0693   0.0326   1.0000
  12.250   1.5065   0.04890   0.04160  -0.0673   0.0318   1.0000
  12.500   1.5102   0.05124   0.04415  -0.0653   0.0309   1.0000
  12.750   1.5130   0.05381   0.04694  -0.0635   0.0302   1.0000
  13.000   1.5142   0.05669   0.05004  -0.0617   0.0298   1.0000
  13.250   1.5128   0.05981   0.05338  -0.0601   0.0294   1.0000
  13.500   1.5084   0.06321   0.05702  -0.0586   0.0292   1.0000
  13.750   1.5010   0.06696   0.06100  -0.0573   0.0290   1.0000
  14.000   1.4900   0.07110   0.06542  -0.0565   0.0289   1.0000
  14.250   1.4746   0.07586   0.07045  -0.0561   0.0289   1.0000
  14.500   1.4556   0.08121   0.07609  -0.0565   0.0290   1.0000
  14.750   1.4333   0.08727   0.08244  -0.0577   0.0292   1.0000
  15.000   1.4078   0.09419   0.08963  -0.0600   0.0295   1.0000
  15.250   1.3806   0.10197   0.09770  -0.0635   0.0298   1.0000
  15.500   1.3523   0.11073   0.10672  -0.0681   0.0302   1.0000
  15.750   1.3234   0.12036   0.11658  -0.0739   0.0307   1.0000
  16.000   1.2933   0.13120   0.12764  -0.0810   0.0312   1.0000
  16.250   1.2613   0.14380   0.14042  -0.0898   0.0318   1.0000
  16.500   1.2281   0.15834   0.15509  -0.0999   0.0327   1.0000
  16.750   1.2168   0.16641   0.16318  -0.1035   0.0336   1.0000
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