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GOE 243 (MVA PR.3) AIRFOIL (goe243-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 243 (MVA PR.3) AIRFOIL (goe243-il)
Reynolds number: 200,000
Max Cl/Cd: 70.39 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe243-il-200000.txt
Download as CSV file: xf-goe243-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 243 (MVA PR.3) 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500   0.1631   0.10714   0.10317  -0.1187   0.9024   0.0675
 -10.250   0.1704   0.10460   0.10059  -0.1194   0.8975   0.0693
 -10.000   0.1491   0.10073   0.09675  -0.1254   0.8874   0.0719
  -9.750   0.1691   0.09844   0.09443  -0.1236   0.8824   0.0724
  -9.500   0.1857   0.09649   0.09246  -0.1225   0.8774   0.0733
  -9.250   0.1979   0.09456   0.09054  -0.1226   0.8698   0.0747
  -9.000   0.2053   0.09216   0.08812  -0.1234   0.8637   0.0772
  -8.750   0.1912   0.08764   0.08358  -0.1288   0.8568   0.0802
  -8.500   0.2091   0.08594   0.08188  -0.1273   0.8495   0.0809
  -8.250   0.2237   0.08406   0.07995  -0.1266   0.8433   0.0821
  -8.000   0.2346   0.08202   0.07790  -0.1268   0.8365   0.0839
  -7.750   0.2130   0.07632   0.07222  -0.1348   0.8274   0.0892
  -7.500   0.2345   0.07493   0.07078  -0.1326   0.8224   0.0899
  -7.250   0.2513   0.07357   0.06941  -0.1317   0.8162   0.0911
  -7.000   0.2187   0.06647   0.06235  -0.1431   0.8067   0.0990
  -6.750   0.2435   0.06600   0.06184  -0.1391   0.8023   0.0997
  -6.500   0.2644   0.06519   0.06101  -0.1371   0.7969   0.1008
  -6.250   0.2785   0.06404   0.05988  -0.1363   0.7898   0.1027
  -6.000   0.2752   0.05788   0.05371  -0.1461   0.7834   0.1116
  -5.750   0.3590   0.02967   0.02355  -0.2127   0.7777   0.0735
  -5.500   0.3927   0.02767   0.02128  -0.2153   0.7707   0.0691
  -5.250   0.4304   0.02565   0.01891  -0.2181   0.7652   0.0666
  -5.000   0.4693   0.02410   0.01696  -0.2207   0.7607   0.0655
  -4.750   0.5002   0.02320   0.01594  -0.2215   0.7550   0.0655
  -4.500   0.5290   0.02243   0.01514  -0.2218   0.7481   0.0660
  -4.250   0.5606   0.02165   0.01429  -0.2223   0.7426   0.0668
  -4.000   0.5939   0.02103   0.01357  -0.2232   0.7381   0.0685
  -3.750   0.6213   0.02066   0.01319  -0.2232   0.7307   0.0703
  -3.500   0.6525   0.02021   0.01263  -0.2236   0.7243   0.0717
  -3.250   0.6831   0.01950   0.01199  -0.2238   0.7191   0.0733
  -3.000   0.7115   0.01919   0.01175  -0.2239   0.7121   0.0755
  -2.750   0.7418   0.01886   0.01142  -0.2242   0.7051   0.0783
  -2.500   0.7760   0.01839   0.01096  -0.2254   0.6994   0.0822
  -2.250   0.8083   0.01816   0.01073  -0.2264   0.6922   0.0886
  -2.000   0.8451   0.01763   0.01020  -0.2287   0.6844   0.0995
  -1.750   0.8970   0.01628   0.00928  -0.2351   0.6781   0.3217
  -1.500   0.9227   0.01670   0.00976  -0.2343   0.6699   0.3572
  -1.250   0.9499   0.01694   0.00997  -0.2337   0.6622   0.3742
  -1.000   0.9793   0.01710   0.00998  -0.2337   0.6546   0.3877
  -0.750   1.0022   0.01738   0.01037  -0.2322   0.6447   0.3994
  -0.500   1.0304   0.01762   0.01049  -0.2317   0.6368   0.4134
  -0.250   1.0519   0.01794   0.01092  -0.2301   0.6262   0.4227
   0.000   1.0826   0.01796   0.01073  -0.2305   0.6179   0.4316
   0.250   1.1049   0.01818   0.01104  -0.2291   0.6082   0.4368
   0.500   1.1320   0.01828   0.01106  -0.2287   0.5996   0.4420
   0.750   1.1594   0.01833   0.01104  -0.2287   0.5900   0.4468
   1.000   1.1887   0.01831   0.01083  -0.2292   0.5806   0.4521
   1.250   1.2145   0.01838   0.01088  -0.2288   0.5710   0.4559
   1.500   1.2394   0.01853   0.01099  -0.2281   0.5616   0.4598
   1.750   1.2647   0.01874   0.01114  -0.2276   0.5528   0.4649
   2.000   1.2905   0.01889   0.01122  -0.2273   0.5436   0.4715
   2.250   1.3175   0.01906   0.01125  -0.2272   0.5354   0.4773
   2.500   1.3395   0.01930   0.01154  -0.2261   0.5262   0.4814
   3.000   1.3882   0.01982   0.01195  -0.2249   0.5102   0.4942
   3.250   1.4127   0.02007   0.01213  -0.2243   0.5029   0.5003
   3.500   1.4355   0.02042   0.01247  -0.2234   0.4959   0.5054
   3.750   1.4565   0.02075   0.01282  -0.2222   0.4883   0.5126
   4.000   1.4817   0.02106   0.01300  -0.2219   0.4817   0.5212
   4.250   1.5020   0.02144   0.01343  -0.2205   0.4752   0.5261
   4.500   1.5218   0.02181   0.01383  -0.2192   0.4685   0.5329
   4.750   1.5466   0.02216   0.01405  -0.2188   0.4626   0.5422
   5.000   1.5664   0.02257   0.01450  -0.2175   0.4570   0.5472
   5.250   1.5830   0.02298   0.01497  -0.2156   0.4505   0.5544
   5.500   1.6034   0.02336   0.01527  -0.2145   0.4443   0.5635
   5.750   1.6212   0.02381   0.01573  -0.2128   0.4388   0.5692
   6.000   1.6332   0.02427   0.01627  -0.2103   0.4330   0.5770
   6.250   1.6507   0.02473   0.01672  -0.2087   0.4274   0.5846
   6.500   1.6740   0.02517   0.01707  -0.2081   0.4222   0.5912
   6.750   1.6868   0.02577   0.01777  -0.2060   0.4170   0.6000
   7.000   1.7000   0.02634   0.01842  -0.2039   0.4115   0.6059
   7.250   1.7169   0.02689   0.01895  -0.2023   0.4062   0.6135
   7.500   1.7352   0.02747   0.01949  -0.2012   0.4009   0.6220
   7.750   1.7439   0.02822   0.02038  -0.1986   0.3953   0.6277
   8.000   1.7562   0.02894   0.02113  -0.1966   0.3895   0.6353
   8.250   1.7750   0.02950   0.02159  -0.1956   0.3839   0.6423
   8.500   1.7802   0.03050   0.02277  -0.1928   0.3781   0.6485
   8.750   1.7894   0.03146   0.02377  -0.1907   0.3719   0.6565
   9.000   1.8025   0.03223   0.02449  -0.1890   0.3661   0.6623
   9.250   1.8081   0.03342   0.02582  -0.1866   0.3597   0.6686
   9.500   1.8144   0.03466   0.02712  -0.1845   0.3526   0.6756
   9.750   1.8230   0.03577   0.02819  -0.1825   0.3460   0.6811
  10.000   1.8248   0.03740   0.02998  -0.1802   0.3378   0.6873
  10.250   1.8293   0.03892   0.03144  -0.1782   0.3298   0.6934
  10.500   1.8295   0.04083   0.03348  -0.1760   0.3202   0.6984
  10.750   1.8293   0.04282   0.03541  -0.1738   0.3108   0.7041
  11.000   1.8271   0.04524   0.03791  -0.1718   0.2992   0.7097
  11.250   1.8242   0.04772   0.04041  -0.1698   0.2881   0.7141
  11.500   1.8200   0.05043   0.04303  -0.1678   0.2776   0.7190
  11.750   1.8185   0.05311   0.04576  -0.1663   0.2671   0.7245
  12.000   1.8167   0.05577   0.04835  -0.1647   0.2592   0.7292
  12.250   1.8180   0.05821   0.05083  -0.1634   0.2518   0.7345
  12.500   1.8190   0.06066   0.05320  -0.1620   0.2463   0.7400
  12.750   1.8242   0.06276   0.05534  -0.1609   0.2416   0.7454
  13.000   1.8291   0.06489   0.05753  -0.1599   0.2375   0.7511
  13.250   1.8349   0.06691   0.05953  -0.1589   0.2340   0.7574
  13.500   1.8438   0.06847   0.06104  -0.1579   0.2311   0.7635
  13.750   1.8543   0.06992   0.06249  -0.1569   0.2285   0.7705
  14.000   1.8617   0.07185   0.06451  -0.1562   0.2263   0.7773
  14.250   1.8698   0.07366   0.06641  -0.1554   0.2242   0.7848
  14.500   1.8785   0.07539   0.06822  -0.1547   0.2222   0.7928
  14.750   1.8876   0.07704   0.06993  -0.1539   0.2203   0.8024
  15.000   1.8980   0.07851   0.07145  -0.1533   0.2185   0.8147
  15.500   1.9269   0.07986   0.07285  -0.1515   0.2154   1.0000
  15.750   1.9440   0.08060   0.07360  -0.1508   0.2142   1.0000
  16.000   1.9496   0.08283   0.07595  -0.1503   0.2132   1.0000
  16.250   1.9551   0.08504   0.07829  -0.1498   0.2123   1.0000
  16.500   1.9607   0.08724   0.08061  -0.1493   0.2113   1.0000
  16.750   1.9660   0.08946   0.08294  -0.1489   0.2103   1.0000
  17.000   1.9706   0.09177   0.08536  -0.1485   0.2094   1.0000
  17.250   1.9749   0.09412   0.08782  -0.1481   0.2085   1.0000
  17.500   1.9791   0.09648   0.09030  -0.1478   0.2076   1.0000
  17.750   1.9822   0.09898   0.09291  -0.1476   0.2068   1.0000
  18.000   1.9850   0.10152   0.09556  -0.1474   0.2060   1.0000
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