Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 233 (MVA CA4) AIRFOIL (goe233-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 233 (MVA CA4) AIRFOIL (goe233-il)
Reynolds number: 100,000
Max Cl/Cd: 60.92 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe233-il-100000.txt
Download as CSV file: xf-goe233-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2805   0.13103   0.12650  -0.0282   1.0000   0.0973
  -9.250  -0.3036   0.13264   0.12821  -0.0271   1.0000   0.0985
  -9.000  -0.3237   0.13442   0.13008  -0.0306   0.9967   0.0990
  -8.750  -0.2780   0.12456   0.12016  -0.0287   0.9961   0.1019
  -8.500  -0.2554   0.12081   0.11637  -0.0323   0.9919   0.1054
  -8.250  -0.2400   0.11789   0.11345  -0.0378   0.9859   0.1102
  -8.000  -0.2559   0.11999   0.11561  -0.0476   0.9733   0.1124
  -7.750  -0.2090   0.11073   0.10628  -0.0467   0.9739   0.1148
  -7.500  -0.1816   0.10707   0.10258  -0.0499   0.9702   0.1199
  -7.250  -0.1846   0.10687   0.10241  -0.0549   0.9583   0.1255
  -7.000  -0.1778   0.10390   0.09947  -0.0592   0.9491   0.1274
  -6.750  -0.1448   0.09892   0.09444  -0.0590   0.9462   0.1306
  -6.500  -0.1226   0.09593   0.09143  -0.0626   0.9405   0.1357
  -6.250  -0.1211   0.09552   0.09106  -0.0759   0.9246   0.1418
  -6.000  -0.0938   0.09025   0.08575  -0.0725   0.9232   0.1439
  -5.750  -0.0827   0.08813   0.08363  -0.0707   0.9145   0.1472
  -5.250   0.0952   0.04004   0.03428  -0.1721   0.9056   0.0871
  -5.000   0.1686   0.03372   0.02704  -0.1890   0.9012   0.0876
  -4.750   0.2114   0.03190   0.02503  -0.1935   0.8955   0.0909
  -4.500   0.2651   0.02985   0.02263  -0.1994   0.8925   0.0938
  -4.250   0.3184   0.02827   0.02075  -0.2043   0.8903   0.0981
  -4.000   0.3446   0.02788   0.02045  -0.2042   0.8819   0.1027
  -3.750   0.3869   0.02716   0.01972  -0.2068   0.8771   0.1145
  -3.500   0.4392   0.02588   0.01856  -0.2116   0.8743   0.1557
  -3.250   0.4627   0.02653   0.01969  -0.2106   0.8652   0.2230
  -3.000   0.4904   0.02770   0.02086  -0.2089   0.8591   0.2514
  -2.750   0.5142   0.02897   0.02215  -0.2065   0.8528   0.2664
  -2.500   0.5250   0.03078   0.02411  -0.2015   0.8436   0.2711
  -2.250   0.5574   0.03137   0.02465  -0.2006   0.8401   0.2849
  -2.000   0.5785   0.03180   0.02496  -0.2002   0.8302   0.2979
  -1.750   0.6014   0.03266   0.02590  -0.1972   0.8253   0.3071
  -1.500   0.6394   0.03268   0.02580  -0.1981   0.8224   0.3293
  -1.250   0.6411   0.03402   0.02729  -0.1927   0.8109   0.3349
  -1.000   0.6743   0.03379   0.02701  -0.1927   0.8073   0.3523
  -0.750   0.6933   0.03424   0.02745  -0.1916   0.7984   0.3665
  -0.500   0.7271   0.03377   0.02690  -0.1926   0.7931   0.3821
  -0.250   0.7698   0.03277   0.02577  -0.1953   0.7900   0.3967
   0.000   0.7926   0.03310   0.02604  -0.1955   0.7804   0.4098
   0.250   0.8287   0.03254   0.02539  -0.1970   0.7757   0.4245
   0.500   0.8657   0.03173   0.02453  -0.1980   0.7725   0.4363
   0.750   0.8825   0.03227   0.02509  -0.1971   0.7620   0.4443
   1.000   0.9212   0.03158   0.02430  -0.1988   0.7579   0.4569
   1.250   0.9615   0.03085   0.02347  -0.2005   0.7548   0.4690
   1.500   0.9745   0.03163   0.02434  -0.1989   0.7437   0.4754
   1.750   1.0151   0.03087   0.02348  -0.2006   0.7398   0.4864
   2.000   1.0329   0.03129   0.02398  -0.1993   0.7295   0.4944
   2.250   1.0710   0.03038   0.02300  -0.2002   0.7243   0.5049
   2.500   1.0961   0.03047   0.02311  -0.1999   0.7152   0.5097
   2.750   1.1313   0.02995   0.02252  -0.2008   0.7088   0.5137
   3.000   1.1640   0.02971   0.02222  -0.2014   0.7019   0.5168
   3.250   1.1915   0.02957   0.02210  -0.2013   0.6933   0.5187
   3.500   1.2305   0.02863   0.02110  -0.2022   0.6888   0.5219
   3.750   1.2502   0.02912   0.02167  -0.2012   0.6774   0.5251
   4.000   1.2904   0.02815   0.02059  -0.2023   0.6721   0.5288
   4.250   1.3104   0.02867   0.02120  -0.2013   0.6607   0.5304
   4.500   1.3481   0.02808   0.02053  -0.2022   0.6557   0.5328
   4.750   1.3658   0.02875   0.02135  -0.2009   0.6449   0.5354
   5.000   1.4023   0.02815   0.02073  -0.2016   0.6393   0.5401
   5.250   1.4212   0.02877   0.02148  -0.2004   0.6282   0.5435
   5.500   1.4584   0.02821   0.02082  -0.2011   0.6218   0.5472
   5.750   1.4774   0.02873   0.02148  -0.1998   0.6103   0.5497
   6.000   1.5055   0.02867   0.02148  -0.1994   0.6016   0.5534
   6.250   1.5321   0.02868   0.02154  -0.1988   0.5917   0.5582
   6.500   1.5547   0.02896   0.02191  -0.1978   0.5808   0.5631
   6.750   1.5890   0.02841   0.02132  -0.1980   0.5718   0.5685
   7.000   1.6073   0.02871   0.02177  -0.1962   0.5584   0.5729
   7.250   1.6292   0.02883   0.02197  -0.1948   0.5451   0.5775
   7.500   1.6526   0.02879   0.02201  -0.1935   0.5315   0.5827
   7.750   1.6750   0.02865   0.02192  -0.1920   0.5158   0.5893
   8.000   1.6950   0.02848   0.02176  -0.1900   0.4970   0.5964
   8.250   1.7142   0.02817   0.02141  -0.1878   0.4758   0.6036
   8.500   1.7276   0.02836   0.02160  -0.1849   0.4533   0.6108
   8.750   1.7393   0.02879   0.02205  -0.1820   0.4316   0.6177
   9.000   1.7514   0.02933   0.02256  -0.1792   0.4115   0.6265
   9.250   1.7620   0.02997   0.02318  -0.1763   0.3923   0.6370
   9.500   1.7672   0.03084   0.02412  -0.1728   0.3737   0.6492
   9.750   1.7697   0.03174   0.02513  -0.1689   0.3571   0.6652
  10.000   1.7728   0.03271   0.02626  -0.1653   0.3412   0.6988
  10.250   1.7708   0.03381   0.02744  -0.1611   0.3269   1.0000
  10.500   1.7705   0.03530   0.02894  -0.1576   0.3113   1.0000
  10.750   1.7685   0.03703   0.03066  -0.1542   0.2953   1.0000
  11.000   1.7646   0.03903   0.03266  -0.1508   0.2788   1.0000
  11.250   1.7583   0.04137   0.03501  -0.1476   0.2614   1.0000
  11.500   1.7487   0.04416   0.03778  -0.1445   0.2421   1.0000
  11.750   1.7348   0.04752   0.04107  -0.1415   0.2209   1.0000
  12.000   1.7174   0.05153   0.04508  -0.1388   0.1957   1.0000
  12.250   1.6970   0.05619   0.04968  -0.1366   0.1661   1.0000
  12.500   1.6772   0.06112   0.05444  -0.1348   0.1405   1.0000
  12.750   1.6607   0.06590   0.05904  -0.1333   0.1234   1.0000
  13.000   1.6478   0.07038   0.06339  -0.1320   0.1124   1.0000
  13.250   1.6362   0.07470   0.06756  -0.1307   0.1046   1.0000
  13.500   1.6321   0.07821   0.07111  -0.1295   0.0972   1.0000
  13.750   1.6279   0.08149   0.07422  -0.1279   0.0916   1.0000
  14.000   1.6287   0.08442   0.07725  -0.1267   0.0863   1.0000
  14.250   1.6325   0.08658   0.07927  -0.1249   0.0814   1.0000
  14.500   1.6398   0.08858   0.08134  -0.1232   0.0773   1.0000
  14.750   1.6460   0.09078   0.08359  -0.1218   0.0734   1.0000
  15.000   1.6690   0.09068   0.08322  -0.1188   0.0687   1.0000
  15.250   1.6730   0.09349   0.08628  -0.1178   0.0666   1.0000
  15.500   1.6783   0.09614   0.08913  -0.1169   0.0642   1.0000
  15.750   1.6873   0.09827   0.09130  -0.1158   0.0616   1.0000
  16.000   1.7141   0.09905   0.09196  -0.1133   0.0584   1.0000
  16.250   1.7079   0.10314   0.09638  -0.1133   0.0576   1.0000
  16.500   1.7012   0.10748   0.10101  -0.1134   0.0569   1.0000
  16.750   1.6920   0.11221   0.10604  -0.1141   0.0562   1.0000
  17.000   1.6810   0.11730   0.11142  -0.1152   0.0555   1.0000
  17.250   1.6681   0.12280   0.11720  -0.1169   0.0550   1.0000
  17.500   1.6531   0.12880   0.12348  -0.1193   0.0545   1.0000
  17.750   1.6351   0.13559   0.13055  -0.1225   0.0543   1.0000
  18.000   1.6134   0.14344   0.13870  -0.1269   0.0543   1.0000
  18.250   1.5861   0.15300   0.14858  -0.1331   0.0547   1.0000
  18.500   1.5523   0.16498   0.16088  -0.1416   0.0556   1.0000
  18.750   1.5156   0.17912   0.17529  -0.1522   0.0569   1.0000
  19.000   1.4812   0.19434   0.19068  -0.1636   0.0582   1.0000
<< Back to GOE 233 (MVA CA4) AIRFOIL (goe233-il)

Polar data table (+)

Polar graphs


<< Back to GOE 233 (MVA CA4) AIRFOIL (goe233-il)