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GOE 233 (MVA CA4) AIRFOIL (goe233-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 233 (MVA CA4) AIRFOIL (goe233-il)
Reynolds number: 1,000,000
Max Cl/Cd: 134.95 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe233-il-1000000-n5.txt
Download as CSV file: xf-goe233-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.4816   0.06024   0.05765  -0.0932   0.8745   0.0169
 -11.500  -0.4816   0.05528   0.05259  -0.0987   0.8632   0.0170
 -11.250  -0.4718   0.05071   0.04791  -0.1052   0.8544   0.0171
 -11.000  -0.4561   0.04660   0.04370  -0.1119   0.8460   0.0173
 -10.750  -0.4359   0.04261   0.03960  -0.1192   0.8389   0.0174
 -10.500  -0.4110   0.03882   0.03570  -0.1271   0.8318   0.0176
 -10.000  -0.3478   0.03197   0.02857  -0.1439   0.8190   0.0182
  -9.750  -0.3106   0.02901   0.02545  -0.1524   0.8124   0.0185
  -9.500  -0.2715   0.02638   0.02265  -0.1603   0.8068   0.0190
  -9.250  -0.2319   0.02413   0.02024  -0.1673   0.8016   0.0194
  -9.000  -0.1930   0.02226   0.01822  -0.1732   0.7960   0.0197
  -8.750  -0.1551   0.02071   0.01650  -0.1781   0.7906   0.0199
  -8.500  -0.1184   0.01931   0.01502  -0.1823   0.7855   0.0203
  -8.250  -0.0828   0.01821   0.01384  -0.1857   0.7793   0.0206
  -8.000  -0.0479   0.01725   0.01278  -0.1887   0.7731   0.0208
  -7.750  -0.0131   0.01632   0.01178  -0.1915   0.7669   0.0211
  -7.500   0.0210   0.01550   0.01086  -0.1939   0.7604   0.0214
  -7.250   0.0546   0.01477   0.01003  -0.1960   0.7544   0.0217
  -7.000   0.0879   0.01409   0.00927  -0.1979   0.7476   0.0220
  -6.750   0.1205   0.01350   0.00858  -0.1995   0.7401   0.0224
  -6.500   0.1529   0.01295   0.00796  -0.2009   0.7327   0.0227
  -6.250   0.1848   0.01248   0.00739  -0.2022   0.7241   0.0230
  -6.000   0.2164   0.01206   0.00688  -0.2033   0.7148   0.0232
  -5.750   0.2476   0.01173   0.00644  -0.2042   0.7028   0.0234
  -5.500   0.2786   0.01143   0.00604  -0.2050   0.6899   0.0235
  -5.250   0.3094   0.01116   0.00568  -0.2058   0.6790   0.0237
  -5.000   0.3417   0.01068   0.00510  -0.2070   0.6706   0.0241
  -4.750   0.3732   0.01033   0.00469  -0.2080   0.6629   0.0245
  -4.250   0.4347   0.00986   0.00409  -0.2093   0.6495   0.0253
  -4.000   0.4652   0.00966   0.00382  -0.2099   0.6435   0.0257
  -3.750   0.4955   0.00949   0.00359  -0.2103   0.6378   0.0261
  -3.500   0.5259   0.00932   0.00337  -0.2108   0.6326   0.0264
  -3.250   0.5560   0.00919   0.00319  -0.2112   0.6268   0.0268
  -2.750   0.6157   0.00898   0.00288  -0.2118   0.6156   0.0275
  -2.500   0.6453   0.00891   0.00276  -0.2121   0.6096   0.0278
  -2.000   0.7048   0.00874   0.00250  -0.2126   0.5999   0.0291
  -1.750   0.7343   0.00869   0.00241  -0.2128   0.5936   0.0300
  -1.500   0.7633   0.00869   0.00235  -0.2130   0.5863   0.0312
  -1.250   0.7927   0.00865   0.00229  -0.2131   0.5801   0.0322
  -1.000   0.8219   0.00863   0.00225  -0.2133   0.5750   0.0342
  -0.750   0.8515   0.00853   0.00218  -0.2136   0.5700   0.0636
  -0.500   0.8807   0.00850   0.00216  -0.2137   0.5657   0.0749
  -0.250   0.9099   0.00847   0.00214  -0.2139   0.5603   0.0847
   0.000   0.9394   0.00835   0.00211  -0.2142   0.5544   0.1363
   0.250   0.9684   0.00830   0.00211  -0.2144   0.5476   0.1606
   0.500   0.9975   0.00822   0.00210  -0.2147   0.5384   0.2102
   0.750   1.0261   0.00821   0.00216  -0.2148   0.5298   0.2542
   1.000   1.0542   0.00830   0.00225  -0.2147   0.5202   0.2695
   1.250   1.0824   0.00838   0.00232  -0.2146   0.5121   0.2775
   1.500   1.1102   0.00851   0.00243  -0.2145   0.5026   0.2889
   1.750   1.1379   0.00863   0.00254  -0.2144   0.4914   0.2969
   2.000   1.1654   0.00878   0.00265  -0.2142   0.4802   0.3022
   2.250   1.1926   0.00895   0.00277  -0.2140   0.4693   0.3060
   2.500   1.2200   0.00910   0.00289  -0.2138   0.4584   0.3081
   2.750   1.2471   0.00928   0.00303  -0.2136   0.4471   0.3104
   3.000   1.2739   0.00947   0.00318  -0.2133   0.4361   0.3129
   3.250   1.3009   0.00964   0.00334  -0.2131   0.4258   0.3160
   3.500   1.3273   0.00986   0.00351  -0.2128   0.4139   0.3195
   3.750   1.3535   0.01009   0.00370  -0.2124   0.4026   0.3226
   4.000   1.3803   0.01025   0.00385  -0.2122   0.3938   0.3246
   4.250   1.4065   0.01046   0.00405  -0.2118   0.3843   0.3281
   4.500   1.4321   0.01072   0.00427  -0.2114   0.3702   0.3310
   4.750   1.4566   0.01108   0.00454  -0.2108   0.3469   0.3330
   5.000   1.4791   0.01161   0.00489  -0.2099   0.3126   0.3347
   5.250   1.4993   0.01232   0.00537  -0.2086   0.2721   0.3363
   5.500   1.5206   0.01290   0.00581  -0.2075   0.2455   0.3378
   5.750   1.5439   0.01328   0.00614  -0.2067   0.2331   0.3392
   6.000   1.5668   0.01367   0.00648  -0.2059   0.2218   0.3404
   6.250   1.5897   0.01403   0.00682  -0.2050   0.2123   0.3423
   6.500   1.6128   0.01436   0.00714  -0.2042   0.2048   0.3441
   6.750   1.6362   0.01464   0.00745  -0.2034   0.1994   0.3462
   7.000   1.6583   0.01501   0.00780  -0.2024   0.1929   0.3483
   7.250   1.6811   0.01530   0.00812  -0.2015   0.1875   0.3503
   7.500   1.7026   0.01566   0.00847  -0.2004   0.1802   0.3521
   7.750   1.7229   0.01607   0.00887  -0.1992   0.1707   0.3537
   8.000   1.7400   0.01666   0.00937  -0.1974   0.1535   0.3550
   8.500   1.7412   0.01922   0.01148  -0.1883   0.0834   0.3570
   8.750   1.7480   0.02028   0.01248  -0.1850   0.0672   0.3586
   9.000   1.7567   0.02129   0.01345  -0.1821   0.0557   0.3601
   9.250   1.7664   0.02227   0.01441  -0.1795   0.0479   0.3619
   9.500   1.7767   0.02325   0.01539  -0.1772   0.0424   0.3638
   9.750   1.7887   0.02414   0.01632  -0.1751   0.0392   0.3657
  10.000   1.7994   0.02517   0.01736  -0.1729   0.0360   0.3674
  10.250   1.8107   0.02618   0.01841  -0.1709   0.0339   0.3690
  10.500   1.8222   0.02721   0.01949  -0.1690   0.0323   0.3704
  10.750   1.8324   0.02837   0.02068  -0.1671   0.0306   0.3716
  11.000   1.8416   0.02965   0.02200  -0.1651   0.0288   0.3733
  11.250   1.8520   0.03085   0.02326  -0.1634   0.0276   0.3751
  11.500   1.8616   0.03216   0.02463  -0.1616   0.0263   0.3770
  11.750   1.8700   0.03361   0.02612  -0.1598   0.0250   0.3791
  12.000   1.8770   0.03520   0.02776  -0.1580   0.0237   0.3812
  12.250   1.8850   0.03672   0.02934  -0.1563   0.0226   0.3832
  12.500   1.8920   0.03837   0.03105  -0.1547   0.0213   0.3849
  12.750   1.8974   0.04021   0.03293  -0.1530   0.0199   0.3864
  13.000   1.9024   0.04212   0.03489  -0.1513   0.0186   0.3879
  13.250   1.9073   0.04407   0.03691  -0.1498   0.0174   0.3898
  13.500   1.9109   0.04622   0.03912  -0.1483   0.0163   0.3917
  13.750   1.9138   0.04852   0.04147  -0.1469   0.0153   0.3937
  14.000   1.9175   0.05077   0.04380  -0.1456   0.0146   0.3958
  14.250   1.9200   0.05319   0.04629  -0.1444   0.0138   0.3979
  14.500   1.9212   0.05580   0.04897  -0.1432   0.0130   0.4001
  14.750   1.9213   0.05862   0.05185  -0.1421   0.0123   0.4021
  15.000   1.9227   0.06134   0.05465  -0.1411   0.0118   0.4045
  15.250   1.9233   0.06417   0.05757  -0.1402   0.0114   0.4071
  15.500   1.9229   0.06716   0.06064  -0.1393   0.0109   0.4096
  15.750   1.9209   0.07039   0.06396  -0.1386   0.0104   0.4120
  16.000   1.9180   0.07381   0.06745  -0.1379   0.0099   0.4145
  16.250   1.9148   0.07730   0.07102  -0.1373   0.0095   0.4168
  16.500   1.9133   0.08059   0.07441  -0.1368   0.0093   0.4196
  16.750   1.9102   0.08412   0.07804  -0.1364   0.0091   0.4228
  17.000   1.9062   0.08783   0.08184  -0.1362   0.0088   0.4263
  17.250   1.9019   0.09161   0.08572  -0.1360   0.0086   0.4300
  17.750   1.8913   0.09960   0.09390  -0.1360   0.0081   0.4383
  18.000   1.8846   0.10385   0.09825  -0.1363   0.0079   0.4436
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