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GOE 233 (MVA CA4) AIRFOIL (goe233-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 233 (MVA CA4) AIRFOIL (goe233-il)
Reynolds number: 200,000
Max Cl/Cd: 87.1 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe233-il-200000-n5.txt
Download as CSV file: xf-goe233-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 233 (MVA CA4) 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.1294   0.10263   0.09882  -0.0762   0.9541   0.0321
  -9.750  -0.1174   0.09945   0.09564  -0.0780   0.9464   0.0316
  -9.500  -0.1119   0.09492   0.09109  -0.0813   0.9381   0.0321
  -9.250  -0.1070   0.09053   0.08668  -0.0841   0.9287   0.0323
  -9.000  -0.0987   0.08732   0.08346  -0.0856   0.9196   0.0321
  -8.750  -0.0918   0.08380   0.07992  -0.0874   0.9106   0.0320
  -8.500  -0.0869   0.07997   0.07608  -0.0894   0.9011   0.0319
  -8.000  -0.1185   0.05898   0.05497  -0.1062   0.8780   0.0323
  -7.750  -0.0560   0.02985   0.02448  -0.1727   0.8656   0.0323
  -7.500  -0.0063   0.02597   0.02013  -0.1838   0.8605   0.0330
  -7.250   0.0262   0.02440   0.01847  -0.1867   0.8541   0.0338
  -7.000   0.0616   0.02286   0.01673  -0.1902   0.8476   0.0346
  -6.750   0.0957   0.02158   0.01526  -0.1927   0.8425   0.0351
  -6.500   0.1283   0.02058   0.01411  -0.1946   0.8358   0.0356
  -6.250   0.1601   0.01975   0.01315  -0.1960   0.8295   0.0361
  -6.000   0.1917   0.01905   0.01231  -0.1971   0.8237   0.0366
  -5.750   0.2232   0.01844   0.01159  -0.1983   0.8163   0.0375
  -5.500   0.2541   0.01791   0.01099  -0.1991   0.8102   0.0383
  -5.250   0.2852   0.01745   0.01051  -0.2001   0.8038   0.0390
  -5.000   0.3174   0.01695   0.00994  -0.2014   0.7968   0.0397
  -4.750   0.3504   0.01642   0.00929  -0.2028   0.7909   0.0404
  -4.500   0.3831   0.01591   0.00870  -0.2043   0.7832   0.0413
  -4.250   0.4157   0.01545   0.00809  -0.2056   0.7765   0.0423
  -4.000   0.4477   0.01505   0.00755  -0.2067   0.7695   0.0434
  -3.500   0.5112   0.01427   0.00660  -0.2087   0.7537   0.0496
  -3.250   0.5424   0.01393   0.00627  -0.2095   0.7452   0.0613
  -3.000   0.5730   0.01369   0.00593  -0.2101   0.7382   0.0809
  -2.750   0.6045   0.01330   0.00562  -0.2111   0.7304   0.1128
  -2.500   0.6347   0.01310   0.00538  -0.2116   0.7238   0.1483
  -2.250   0.6646   0.01294   0.00521  -0.2120   0.7169   0.1715
  -2.000   0.6941   0.01281   0.00517  -0.2124   0.7100   0.2055
  -1.750   0.7226   0.01289   0.00530  -0.2123   0.7038   0.2415
  -1.500   0.7510   0.01297   0.00535  -0.2123   0.6968   0.2606
  -1.250   0.7792   0.01310   0.00541  -0.2121   0.6907   0.2729
  -1.000   0.8074   0.01325   0.00553  -0.2119   0.6847   0.2840
  -0.750   0.8354   0.01341   0.00564  -0.2117   0.6783   0.2957
  -0.500   0.8632   0.01362   0.00576  -0.2114   0.6727   0.3060
  -0.250   0.8905   0.01387   0.00603  -0.2110   0.6660   0.3136
   0.000   0.9182   0.01404   0.00614  -0.2107   0.6593   0.3203
   0.250   0.9464   0.01412   0.00612  -0.2106   0.6528   0.3255
   0.500   0.9736   0.01429   0.00631  -0.2103   0.6451   0.3287
   0.750   1.0009   0.01448   0.00643  -0.2099   0.6383   0.3337
   1.000   1.0290   0.01456   0.00645  -0.2099   0.6309   0.3404
   1.250   1.0560   0.01472   0.00663  -0.2095   0.6242   0.3431
   1.500   1.0831   0.01486   0.00677  -0.2092   0.6175   0.3461
   1.750   1.1104   0.01497   0.00687  -0.2090   0.6099   0.3495
   2.000   1.1379   0.01510   0.00691  -0.2088   0.6032   0.3538
   2.250   1.1652   0.01518   0.00702  -0.2086   0.5962   0.3573
   2.500   1.1921   0.01532   0.00717  -0.2083   0.5896   0.3595
   2.750   1.2189   0.01544   0.00731  -0.2080   0.5825   0.3617
   3.000   1.2456   0.01554   0.00742  -0.2078   0.5745   0.3638
   3.250   1.2724   0.01567   0.00754  -0.2075   0.5676   0.3662
   3.500   1.2988   0.01578   0.00767  -0.2072   0.5591   0.3691
   3.750   1.3249   0.01593   0.00777  -0.2067   0.5501   0.3721
   4.000   1.3505   0.01606   0.00797  -0.2062   0.5401   0.3738
   4.250   1.3759   0.01621   0.00816  -0.2057   0.5309   0.3756
   4.500   1.4012   0.01639   0.00835  -0.2052   0.5215   0.3776
   4.750   1.4265   0.01656   0.00858  -0.2047   0.5126   0.3799
   5.000   1.4513   0.01677   0.00879  -0.2041   0.5034   0.3824
   5.250   1.4761   0.01698   0.00904  -0.2035   0.4935   0.3851
   5.500   1.5001   0.01723   0.00929  -0.2027   0.4836   0.3878
   5.750   1.5234   0.01749   0.00961  -0.2019   0.4722   0.3899
   6.000   1.5463   0.01778   0.00994  -0.2010   0.4605   0.3923
   6.250   1.5685   0.01811   0.01029  -0.1999   0.4490   0.3947
   6.750   1.6103   0.01890   0.01110  -0.1975   0.4219   0.3998
   7.000   1.6289   0.01940   0.01156  -0.1959   0.4046   0.4023
   7.250   1.6455   0.01997   0.01210  -0.1940   0.3838   0.4044
   7.500   1.6598   0.02063   0.01274  -0.1917   0.3581   0.4068
   7.750   1.6697   0.02149   0.01348  -0.1888   0.3271   0.4092
   8.000   1.6741   0.02251   0.01436  -0.1850   0.2973   0.4116
   8.250   1.6772   0.02359   0.01534  -0.1811   0.2765   0.4139
   8.500   1.6848   0.02465   0.01635  -0.1782   0.2621   0.4162
   8.750   1.6928   0.02575   0.01745  -0.1754   0.2503   0.4184
   9.000   1.6995   0.02697   0.01867  -0.1726   0.2396   0.4203
   9.250   1.7083   0.02810   0.01985  -0.1702   0.2299   0.4225
   9.500   1.7156   0.02938   0.02117  -0.1678   0.2211   0.4249
   9.750   1.7232   0.03070   0.02253  -0.1654   0.2115   0.4278
  10.000   1.7311   0.03203   0.02393  -0.1633   0.2027   0.4309
  10.250   1.7373   0.03355   0.02548  -0.1610   0.1928   0.4338
  10.500   1.7454   0.03495   0.02696  -0.1591   0.1807   0.4365
  10.750   1.7503   0.03667   0.02871  -0.1570   0.1647   0.4392
  11.000   1.7504   0.03887   0.03086  -0.1547   0.1405   0.4416
  11.250   1.7414   0.04201   0.03380  -0.1520   0.1092   0.4436
  11.500   1.7317   0.04535   0.03700  -0.1494   0.0880   0.4456
  11.750   1.7261   0.04839   0.04002  -0.1473   0.0758   0.4479
  12.000   1.7225   0.05134   0.04300  -0.1454   0.0676   0.4502
  12.250   1.7199   0.05426   0.04599  -0.1438   0.0613   0.4528
  12.500   1.7185   0.05715   0.04897  -0.1424   0.0568   0.4559
  12.750   1.7169   0.06017   0.05208  -0.1412   0.0529   0.4594
  13.000   1.7130   0.06355   0.05552  -0.1400   0.0499   0.4629
  13.250   1.7128   0.06653   0.05865  -0.1391   0.0472   0.4667
  13.500   1.7106   0.06984   0.06208  -0.1383   0.0449   0.4706
  13.750   1.7062   0.07351   0.06584  -0.1376   0.0429   0.4746
  14.000   1.7013   0.07733   0.06976  -0.1370   0.0412   0.4788
  14.250   1.6996   0.08076   0.07334  -0.1365   0.0394   0.4836
  14.500   1.6965   0.08442   0.07715  -0.1362   0.0377   0.4892
  14.750   1.6916   0.08842   0.08126  -0.1360   0.0363   0.4956
  15.000   1.6845   0.09280   0.08575  -0.1360   0.0351   0.5026
  15.500   1.6762   0.10086   0.09412  -0.1363   0.0326   0.5308
  15.750   1.6732   0.10458   0.09827  -0.1366   0.0313   0.8378
  16.000   1.6660   0.10860   0.10240  -0.1368   0.0303   1.0000
  16.250   1.6601   0.11307   0.10695  -0.1374   0.0293   1.0000
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