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GOE 243 (MVA PR.3) AIRFOIL (goe243-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 243 (MVA PR.3) AIRFOIL (goe243-il)
Reynolds number: 1,000,000
Max Cl/Cd: 119.07 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe243-il-1000000.txt
Download as CSV file: xf-goe243-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000   0.1629   0.09525   0.09257  -0.1067   0.7661   0.0297
 -10.750  -0.1486   0.04983   0.04670  -0.1379   0.7905   0.0286
 -10.500  -0.1730   0.04214   0.03875  -0.1476   0.7825   0.0286
 -10.250  -0.1781   0.03679   0.03319  -0.1563   0.7760   0.0285
 -10.000  -0.1628   0.03168   0.02784  -0.1675   0.7699   0.0286
  -9.750  -0.1360   0.02739   0.02328  -0.1777   0.7637   0.0287
  -9.500  -0.1045   0.02476   0.02045  -0.1842   0.7572   0.0288
  -9.250  -0.0711   0.02298   0.01858  -0.1889   0.7513   0.0290
  -9.000  -0.0373   0.02159   0.01708  -0.1928   0.7444   0.0292
  -8.750  -0.0033   0.02047   0.01582  -0.1962   0.7377   0.0294
  -8.500   0.0317   0.01939   0.01469  -0.1994   0.7335   0.0295
  -8.250   0.0662   0.01845   0.01367  -0.2022   0.7283   0.0297
  -8.000   0.1000   0.01765   0.01278  -0.2046   0.7229   0.0299
  -7.750   0.1333   0.01695   0.01198  -0.2066   0.7171   0.0301
  -7.500   0.1670   0.01625   0.01124  -0.2085   0.7128   0.0303
  -7.250   0.2004   0.01564   0.01057  -0.2103   0.7076   0.0305
  -7.000   0.2333   0.01510   0.00996  -0.2118   0.7021   0.0308
  -6.750   0.2662   0.01463   0.00940  -0.2132   0.6963   0.0310
  -6.500   0.2997   0.01414   0.00889  -0.2148   0.6918   0.0313
  -6.250   0.3332   0.01372   0.00841  -0.2162   0.6865   0.0317
  -6.000   0.3664   0.01336   0.00798  -0.2176   0.6807   0.0320
  -5.750   0.3998   0.01309   0.00764  -0.2190   0.6752   0.0323
  -5.500   0.4341   0.01255   0.00708  -0.2207   0.6700   0.0328
  -5.250   0.4688   0.01210   0.00661  -0.2225   0.6644   0.0333
  -5.000   0.5025   0.01181   0.00627  -0.2240   0.6581   0.0338
  -4.750   0.5365   0.01152   0.00595  -0.2255   0.6530   0.0343
  -4.500   0.5701   0.01125   0.00566  -0.2268   0.6467   0.0348
  -4.250   0.6030   0.01105   0.00539  -0.2280   0.6394   0.0353
  -4.000   0.6360   0.01084   0.00513  -0.2292   0.6329   0.0359
  -3.750   0.6686   0.01067   0.00491  -0.2302   0.6253   0.0364
  -3.500   0.7006   0.01053   0.00468  -0.2311   0.6168   0.0370
  -3.250   0.7347   0.01024   0.00437  -0.2326   0.6096   0.0381
  -3.000   0.7662   0.01014   0.00421  -0.2333   0.6017   0.0391
  -2.750   0.7973   0.01007   0.00409  -0.2340   0.5945   0.0403
  -2.500   0.8285   0.00999   0.00398  -0.2346   0.5864   0.0416
  -2.250   0.8591   0.00995   0.00386  -0.2352   0.5767   0.0440
  -2.000   0.8898   0.00991   0.00379  -0.2357   0.5675   0.0464
  -1.750   0.9197   0.00990   0.00372  -0.2361   0.5569   0.0514
  -1.500   0.9508   0.00982   0.00367  -0.2368   0.5475   0.0667
  -1.250   0.9812   0.00976   0.00363  -0.2374   0.5371   0.1015
  -1.000   1.0162   0.00924   0.00348  -0.2395   0.5266   0.2714
  -0.750   1.0444   0.00936   0.00357  -0.2395   0.5150   0.2922
  -0.500   1.0720   0.00953   0.00367  -0.2394   0.5019   0.3047
  -0.250   1.1000   0.00966   0.00378  -0.2394   0.4904   0.3162
   0.000   1.1267   0.00988   0.00391  -0.2391   0.4784   0.3228
   0.250   1.1544   0.01002   0.00402  -0.2390   0.4678   0.3310
   0.500   1.1811   0.01023   0.00416  -0.2388   0.4580   0.3388
   0.750   1.2084   0.01039   0.00429  -0.2386   0.4492   0.3461
   1.000   1.2346   0.01060   0.00446  -0.2383   0.4403   0.3553
   1.250   1.2618   0.01075   0.00459  -0.2381   0.4334   0.3612
   1.500   1.2878   0.01096   0.00474  -0.2377   0.4256   0.3665
   1.750   1.3144   0.01113   0.00490  -0.2375   0.4189   0.3734
   2.000   1.3407   0.01130   0.00505  -0.2372   0.4121   0.3785
   2.250   1.3653   0.01156   0.00524  -0.2366   0.4043   0.3829
   2.500   1.3914   0.01172   0.00539  -0.2363   0.3983   0.3871
   2.750   1.4168   0.01191   0.00557  -0.2358   0.3917   0.3947
   3.000   1.4406   0.01217   0.00579  -0.2351   0.3852   0.4013
   3.250   1.4659   0.01234   0.00596  -0.2347   0.3809   0.4070
   3.500   1.4907   0.01252   0.00615  -0.2341   0.3759   0.4147
   3.750   1.5139   0.01276   0.00638  -0.2333   0.3703   0.4223
   4.000   1.5351   0.01305   0.00664  -0.2322   0.3645   0.4289
   4.250   1.5563   0.01322   0.00684  -0.2309   0.3602   0.4371
   4.500   1.5762   0.01349   0.00711  -0.2295   0.3543   0.4456
   4.750   1.5951   0.01389   0.00746  -0.2280   0.3473   0.4527
   5.000   1.6177   0.01414   0.00774  -0.2272   0.3424   0.4625
   5.250   1.6385   0.01447   0.00808  -0.2261   0.3366   0.4717
   5.500   1.6566   0.01494   0.00851  -0.2246   0.3294   0.4803
   5.750   1.6777   0.01527   0.00887  -0.2236   0.3239   0.4897
   6.000   1.6961   0.01573   0.00931  -0.2221   0.3168   0.4970
   6.250   1.7138   0.01625   0.00982  -0.2207   0.3095   0.5047
   6.500   1.7317   0.01676   0.01032  -0.2192   0.3015   0.5121
   6.750   1.7468   0.01743   0.01093  -0.2174   0.2922   0.5181
   7.000   1.7613   0.01814   0.01161  -0.2156   0.2810   0.5239
   7.250   1.7739   0.01898   0.01241  -0.2136   0.2677   0.5295
   7.500   1.7817   0.02013   0.01345  -0.2109   0.2500   0.5349
   7.750   1.7841   0.02166   0.01483  -0.2077   0.2271   0.5392
   8.000   1.7825   0.02352   0.01653  -0.2042   0.2019   0.5430
   8.250   1.7860   0.02512   0.01806  -0.2014   0.1879   0.5473
   8.500   1.7946   0.02642   0.01935  -0.1994   0.1811   0.5515
   8.750   1.8046   0.02766   0.02058  -0.1975   0.1769   0.5556
   9.000   1.8134   0.02902   0.02194  -0.1957   0.1728   0.5592
   9.250   1.8255   0.03016   0.02310  -0.1942   0.1707   0.5622
   9.500   1.8375   0.03132   0.02431  -0.1928   0.1694   0.5666
   9.750   1.8494   0.03250   0.02554  -0.1914   0.1680   0.5704
  10.000   1.8596   0.03386   0.02694  -0.1899   0.1668   0.5742
  10.250   1.8702   0.03521   0.02832  -0.1885   0.1656   0.5777
  10.500   1.8790   0.03675   0.02989  -0.1870   0.1644   0.5805
  10.750   1.8881   0.03828   0.03146  -0.1857   0.1632   0.5832
  11.000   1.8955   0.04001   0.03324  -0.1842   0.1621   0.5866
  11.250   1.9028   0.04175   0.03502  -0.1828   0.1609   0.5899
  11.500   1.9080   0.04374   0.03707  -0.1813   0.1597   0.5929
  11.750   1.9138   0.04568   0.03907  -0.1799   0.1587   0.5959
  12.000   1.9187   0.04778   0.04122  -0.1786   0.1580   0.5987
  12.250   1.9276   0.04945   0.04295  -0.1775   0.1577   0.6011
  12.500   1.9348   0.05136   0.04493  -0.1764   0.1575   0.6044
  12.750   1.9427   0.05319   0.04683  -0.1754   0.1572   0.6075
  13.000   1.9492   0.05519   0.04890  -0.1743   0.1568   0.6104
  13.250   1.9556   0.05722   0.05100  -0.1733   0.1564   0.6132
  13.500   1.9615   0.05932   0.05316  -0.1723   0.1560   0.6160
  13.750   1.9658   0.06158   0.05550  -0.1713   0.1557   0.6185
  14.000   1.9707   0.06379   0.05776  -0.1704   0.1553   0.6207
  14.250   1.9739   0.06625   0.06031  -0.1695   0.1549   0.6237
  14.500   1.9786   0.06852   0.06265  -0.1686   0.1545   0.6265
  14.750   1.9808   0.07112   0.06533  -0.1677   0.1539   0.6292
  15.000   1.9848   0.07348   0.06775  -0.1670   0.1533   0.6320
  15.250   1.9864   0.07616   0.07049  -0.1662   0.1526   0.6346
  15.500   1.9889   0.07872   0.07311  -0.1654   0.1519   0.6372
  15.750   1.9897   0.08151   0.07596  -0.1647   0.1513   0.6396
  16.000   1.9905   0.08432   0.07885  -0.1641   0.1506   0.6428
  16.250   1.9907   0.08719   0.08179  -0.1635   0.1498   0.6457
  16.500   1.9889   0.09032   0.08498  -0.1629   0.1488   0.6483
  16.750   1.9883   0.09325   0.08796  -0.1624   0.1479   0.6509
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