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GOE 195 AIRFOIL (goe195-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 195 AIRFOIL (goe195-il)
Reynolds number: 1,000,000
Max Cl/Cd: 106.06 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe195-il-1000000-n5.txt
Download as CSV file: xf-goe195-il-1000000-n5.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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3609   0.09082   0.08910  -0.0405   0.9953   0.0119
  -9.000  -0.4056   0.02249   0.01959  -0.1285   0.9565   0.0175
  -8.750  -0.3786   0.02042   0.01720  -0.1305   0.9512   0.0179
  -8.500  -0.3520   0.01865   0.01520  -0.1321   0.9461   0.0182
  -8.250  -0.3250   0.01812   0.01460  -0.1324   0.9398   0.0184
  -8.000  -0.2977   0.01774   0.01416  -0.1326   0.9332   0.0186
  -7.750  -0.2705   0.01732   0.01367  -0.1328   0.9260   0.0189
  -7.500  -0.2434   0.01668   0.01292  -0.1330   0.9187   0.0191
  -7.250  -0.2162   0.01601   0.01212  -0.1333   0.9110   0.0193
  -7.000  -0.1891   0.01534   0.01131  -0.1335   0.9021   0.0197
  -6.750  -0.1617   0.01477   0.01061  -0.1337   0.8929   0.0201
  -6.500  -0.1344   0.01405   0.00973  -0.1338   0.8823   0.0204
  -6.250  -0.1072   0.01334   0.00884  -0.1339   0.8686   0.0208
  -6.000  -0.0799   0.01273   0.00805  -0.1339   0.8527   0.0211
  -5.750  -0.0527   0.01220   0.00735  -0.1338   0.8344   0.0214
  -5.500  -0.0254   0.01183   0.00681  -0.1337   0.8146   0.0217
  -5.250   0.0018   0.01161   0.00643  -0.1335   0.7932   0.0220
  -5.000   0.0291   0.01137   0.00604  -0.1333   0.7726   0.0222
  -4.750   0.0568   0.01111   0.00565  -0.1332   0.7580   0.0223
  -4.500   0.0845   0.01034   0.00475  -0.1334   0.7456   0.0227
  -4.250   0.1123   0.00995   0.00426  -0.1334   0.7328   0.0230
  -4.000   0.1404   0.00965   0.00389  -0.1334   0.7217   0.0232
  -3.750   0.1686   0.00940   0.00358  -0.1334   0.7127   0.0235
  -3.500   0.1969   0.00918   0.00330  -0.1334   0.7038   0.0237
  -3.250   0.2253   0.00897   0.00304  -0.1335   0.6950   0.0239
  -3.000   0.2535   0.00880   0.00280  -0.1335   0.6844   0.0242
  -2.750   0.2818   0.00864   0.00258  -0.1335   0.6719   0.0245
  -2.500   0.3100   0.00852   0.00240  -0.1334   0.6571   0.0249
  -2.250   0.3380   0.00844   0.00223  -0.1333   0.6371   0.0254
  -2.000   0.3654   0.00843   0.00207  -0.1332   0.6021   0.0258
  -1.750   0.3926   0.00846   0.00194  -0.1329   0.5695   0.0262
  -1.500   0.4203   0.00846   0.00184  -0.1328   0.5516   0.0266
  -1.250   0.4483   0.00844   0.00175  -0.1328   0.5402   0.0270
  -1.000   0.4763   0.00843   0.00168  -0.1327   0.5310   0.0273
  -0.750   0.5045   0.00840   0.00162  -0.1326   0.5233   0.0276
  -0.500   0.5324   0.00841   0.00158  -0.1325   0.5147   0.0278
  -0.250   0.5606   0.00837   0.00150  -0.1325   0.5061   0.0285
   0.000   0.5885   0.00837   0.00145  -0.1324   0.4980   0.0293
   0.250   0.6168   0.00836   0.00142  -0.1324   0.4911   0.0303
   0.500   0.6448   0.00837   0.00142  -0.1323   0.4858   0.0318
   0.750   0.6730   0.00837   0.00142  -0.1322   0.4814   0.0335
   1.250   0.7293   0.00813   0.00144  -0.1323   0.4675   0.1618
   1.500   0.7575   0.00804   0.00152  -0.1324   0.4613   0.2236
   1.750   0.7852   0.00810   0.00160  -0.1323   0.4517   0.2486
   2.000   0.8129   0.00816   0.00166  -0.1322   0.4388   0.2627
   2.250   0.8404   0.00825   0.00173  -0.1320   0.4251   0.2734
   2.500   0.8678   0.00834   0.00182  -0.1319   0.4115   0.2871
   2.750   0.8947   0.00849   0.00192  -0.1317   0.3905   0.2993
   3.000   0.9211   0.00869   0.00204  -0.1314   0.3642   0.3133
   3.250   0.9471   0.00893   0.00221  -0.1310   0.3368   0.3286
   3.500   0.9728   0.00921   0.00240  -0.1307   0.3079   0.3448
   4.000   1.0227   0.00983   0.00297  -0.1299   0.2387   0.4813
   4.250   1.0482   0.01006   0.00324  -0.1295   0.2142   0.5520
   4.500   1.0733   0.01029   0.00353  -0.1291   0.1893   0.6333
   5.000   1.1178   0.01055   0.00413  -0.1271   0.1278   1.0000
   5.250   1.1425   0.01096   0.00443  -0.1265   0.1094   1.0000
   5.500   1.1676   0.01129   0.00471  -0.1261   0.0984   1.0000
   5.750   1.1930   0.01158   0.00496  -0.1256   0.0895   1.0000
   6.000   1.2180   0.01191   0.00524  -0.1251   0.0806   1.0000
   6.250   1.2422   0.01230   0.00556  -0.1245   0.0666   1.0000
   6.500   1.2632   0.01305   0.00610  -0.1234   0.0362   1.0000
   6.750   1.2876   0.01339   0.00644  -0.1228   0.0320   1.0000
   7.000   1.3121   0.01371   0.00677  -0.1223   0.0303   1.0000
   7.250   1.3361   0.01407   0.00714  -0.1216   0.0285   1.0000
   7.500   1.3596   0.01446   0.00754  -0.1209   0.0265   1.0000
   7.750   1.3830   0.01484   0.00794  -0.1202   0.0249   1.0000
   8.000   1.4069   0.01516   0.00828  -0.1195   0.0242   1.0000
   8.250   1.4303   0.01550   0.00866  -0.1188   0.0230   1.0000
   8.500   1.4530   0.01589   0.00906  -0.1180   0.0214   1.0000
   8.750   1.4747   0.01635   0.00952  -0.1170   0.0196   1.0000
   9.000   1.4969   0.01675   0.00995  -0.1161   0.0186   1.0000
   9.250   1.5186   0.01717   0.01038  -0.1152   0.0173   1.0000
   9.500   1.5394   0.01763   0.01085  -0.1141   0.0157   1.0000
   9.750   1.5596   0.01813   0.01136  -0.1130   0.0143   1.0000
  10.000   1.5795   0.01862   0.01188  -0.1117   0.0133   1.0000
  10.250   1.5983   0.01916   0.01243  -0.1104   0.0122   1.0000
  10.500   1.6158   0.01976   0.01306  -0.1088   0.0112   1.0000
  10.750   1.6331   0.02031   0.01366  -0.1072   0.0107   1.0000
  11.000   1.6478   0.02089   0.01429  -0.1051   0.0102   1.0000
  11.250   1.6612   0.02153   0.01497  -0.1029   0.0096   1.0000
  11.500   1.6736   0.02225   0.01573  -0.1006   0.0090   1.0000
  11.750   1.6845   0.02309   0.01662  -0.0982   0.0084   1.0000
  12.000   1.6963   0.02388   0.01748  -0.0960   0.0081   1.0000
  12.250   1.7075   0.02473   0.01839  -0.0939   0.0078   1.0000
  12.500   1.7180   0.02567   0.01940  -0.0917   0.0075   1.0000
  12.750   1.7274   0.02671   0.02050  -0.0896   0.0073   1.0000
  13.000   1.7361   0.02786   0.02171  -0.0875   0.0070   1.0000
  13.250   1.7435   0.02913   0.02305  -0.0855   0.0067   1.0000
  13.500   1.7498   0.03057   0.02457  -0.0835   0.0065   1.0000
  13.750   1.7542   0.03222   0.02630  -0.0815   0.0062   1.0000
  14.000   1.7588   0.03395   0.02811  -0.0798   0.0061   1.0000
  14.250   1.7639   0.03570   0.02996  -0.0783   0.0060   1.0000
  14.500   1.7678   0.03765   0.03199  -0.0769   0.0058   1.0000
  14.750   1.7706   0.03979   0.03423  -0.0757   0.0057   1.0000
  15.000   1.7725   0.04212   0.03666  -0.0746   0.0056   1.0000
  15.250   1.7733   0.04465   0.03929  -0.0737   0.0055   1.0000
  15.500   1.7727   0.04741   0.04215  -0.0730   0.0054   1.0000
  15.750   1.7713   0.05037   0.04521  -0.0724   0.0052   1.0000
  16.000   1.7689   0.05352   0.04846  -0.0721   0.0051   1.0000
  16.250   1.7650   0.05698   0.05202  -0.0719   0.0050   1.0000
  16.500   1.7599   0.06074   0.05589  -0.0720   0.0049   1.0000
  16.750   1.7539   0.06479   0.06004  -0.0724   0.0048   1.0000
  17.000   1.7461   0.06920   0.06456  -0.0731   0.0047   1.0000
  17.250   1.7368   0.07393   0.06940  -0.0739   0.0046   1.0000
  17.500   1.7258   0.07899   0.07458  -0.0750   0.0046   1.0000
  17.750   1.7132   0.08440   0.08011  -0.0763   0.0045   1.0000
  18.000   1.6989   0.09010   0.08593  -0.0778   0.0044   1.0000
  18.250   1.6826   0.09626   0.09222  -0.0796   0.0044   1.0000
  18.500   1.6670   0.10244   0.09853  -0.0815   0.0043   1.0000
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