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GOE 165 (MVA MK.11) AIRFOIL (goe165-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 165 (MVA MK.11) AIRFOIL (goe165-il)
Reynolds number: 500,000
Max Cl/Cd: 79.06 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe165-il-500000-n5.txt
Download as CSV file: xf-goe165-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 165 (MVA MK.11) AIRFOIL                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2481   0.09286   0.09070  -0.0498   0.9909   0.0067
  -8.750  -0.2363   0.08820   0.08604  -0.0542   0.9885   0.0065
  -8.500  -0.2266   0.08334   0.08120  -0.0583   0.9849   0.0064
  -8.250  -0.2182   0.07785   0.07572  -0.0630   0.9797   0.0065
  -8.000  -0.2160   0.07258   0.07048  -0.0663   0.9714   0.0066
  -7.750  -0.2193   0.06770   0.06564  -0.0684   0.9582   0.0066
  -7.500  -0.2206   0.06089   0.05885  -0.0730   0.9409   0.0065
  -7.250  -0.2095   0.04662   0.04441  -0.0931   0.9238   0.0063
  -7.000  -0.1368   0.02975   0.02673  -0.1322   0.9095   0.0061
  -6.750  -0.0654   0.02263   0.01880  -0.1492   0.8937   0.0059
  -6.500  -0.0122   0.01911   0.01464  -0.1570   0.8567   0.0059
  -6.250   0.0200   0.01742   0.01241  -0.1588   0.7962   0.0059
  -5.750   0.0709   0.01542   0.00963  -0.1586   0.7220   0.0063
  -5.000   0.1527   0.01356   0.00715  -0.1587   0.6754   0.0071
  -4.750   0.1812   0.01271   0.00620  -0.1594   0.6661   0.0078
  -4.250   0.2385   0.01188   0.00516  -0.1600   0.6495   0.0092
  -4.000   0.2673   0.01149   0.00462  -0.1603   0.6417   0.0097
  -3.750   0.2964   0.01115   0.00416  -0.1606   0.6339   0.0104
  -3.500   0.3248   0.01094   0.00382  -0.1607   0.6255   0.0110
  -3.250   0.3540   0.01059   0.00330  -0.1609   0.6168   0.0136
  -3.000   0.3824   0.01043   0.00302  -0.1610   0.6091   0.0158
  -2.750   0.4107   0.01033   0.00281  -0.1610   0.5996   0.0189
  -2.500   0.4388   0.01020   0.00270  -0.1610   0.5879   0.0447
  -2.250   0.4665   0.01015   0.00255  -0.1608   0.5729   0.0540
  -2.000   0.4938   0.01010   0.00243  -0.1607   0.5526   0.0654
  -1.750   0.5201   0.01012   0.00234  -0.1604   0.5155   0.1018
  -1.500   0.5434   0.01044   0.00231  -0.1595   0.4417   0.1176
  -1.250   0.5697   0.01030   0.00226  -0.1596   0.4081   0.2197
  -1.000   0.5964   0.01039   0.00230  -0.1595   0.3891   0.2481
  -0.750   0.6230   0.01049   0.00238  -0.1593   0.3712   0.2812
  -0.250   0.6765   0.01080   0.00259  -0.1588   0.3425   0.3225
   0.000   0.7034   0.01094   0.00269  -0.1585   0.3331   0.3333
   0.500   0.7574   0.01122   0.00288  -0.1580   0.3175   0.3494
   0.750   0.7842   0.01138   0.00301  -0.1578   0.3104   0.3587
   1.000   0.8111   0.01153   0.00312  -0.1575   0.3035   0.3666
   1.250   0.8377   0.01169   0.00326  -0.1572   0.2954   0.3724
   1.500   0.8645   0.01183   0.00337  -0.1570   0.2886   0.3766
   1.750   0.8908   0.01202   0.00347  -0.1566   0.2792   0.3802
   2.000   0.9174   0.01215   0.00361  -0.1564   0.2712   0.3832
   2.250   0.9436   0.01232   0.00375  -0.1560   0.2630   0.3861
   2.500   0.9701   0.01247   0.00388  -0.1557   0.2543   0.3892
   2.750   0.9960   0.01268   0.00403  -0.1553   0.2438   0.3928
   3.000   1.0214   0.01292   0.00419  -0.1549   0.2290   0.3956
   3.250   1.0451   0.01330   0.00444  -0.1542   0.1998   0.3980
   3.500   1.0609   0.01452   0.00520  -0.1523   0.1139   0.4000
   3.750   1.0854   0.01483   0.00548  -0.1517   0.1042   0.4020
   4.000   1.1097   0.01515   0.00577  -0.1511   0.0955   0.4048
   4.250   1.1326   0.01561   0.00614  -0.1502   0.0652   0.4082
   4.500   1.1558   0.01604   0.00653  -0.1494   0.0566   0.4115
   4.750   1.1802   0.01630   0.00684  -0.1488   0.0525   0.4145
   5.000   1.2045   0.01657   0.00718  -0.1481   0.0502   0.4166
   5.250   1.2280   0.01691   0.00758  -0.1474   0.0470   0.4186
   5.500   1.2510   0.01729   0.00799  -0.1465   0.0430   0.4206
   5.750   1.2750   0.01753   0.00826  -0.1459   0.0393   0.4226
   6.000   1.2960   0.01807   0.00869  -0.1448   0.0169   0.4246
   6.250   1.3178   0.01850   0.00918  -0.1437   0.0115   0.4264
   6.500   1.3398   0.01889   0.00970  -0.1427   0.0100   0.4286
   6.750   1.3607   0.01937   0.01029  -0.1415   0.0085   0.4310
   7.000   1.3799   0.01997   0.01101  -0.1400   0.0074   0.4335
   7.250   1.3999   0.02047   0.01159  -0.1386   0.0068   0.4360
   7.500   1.4186   0.02103   0.01225  -0.1371   0.0062   0.4384
   7.750   1.4363   0.02163   0.01292  -0.1354   0.0057   0.4406
   8.000   1.4501   0.02236   0.01375  -0.1331   0.0051   0.4427
   8.250   1.4632   0.02305   0.01455  -0.1306   0.0048   0.4450
   8.500   1.4762   0.02382   0.01545  -0.1282   0.0045   0.4475
   8.750   1.4876   0.02469   0.01643  -0.1256   0.0043   0.4501
   9.000   1.4971   0.02567   0.01751  -0.1228   0.0040   0.4527
   9.250   1.5051   0.02674   0.01869  -0.1199   0.0039   0.4552
   9.500   1.5115   0.02793   0.01999  -0.1170   0.0037   0.4577
   9.750   1.5160   0.02928   0.02146  -0.1140   0.0036   0.4604
  10.000   1.5179   0.03087   0.02316  -0.1110   0.0035   0.4634
  10.250   1.5162   0.03284   0.02526  -0.1079   0.0034   0.4663
  10.500   1.5081   0.03551   0.02807  -0.1047   0.0033   0.4687
  10.750   1.5092   0.03762   0.03031  -0.1028   0.0032   0.4715
  11.000   1.5075   0.04018   0.03302  -0.1011   0.0031   0.4743
  11.250   1.5055   0.04298   0.03596  -0.0998   0.0030   0.4773
  11.500   1.5027   0.04609   0.03922  -0.0989   0.0029   0.4804
  11.750   1.4978   0.04965   0.04293  -0.0984   0.0028   0.4834
  12.000   1.4938   0.05325   0.04667  -0.0982   0.0026   0.4864
  12.250   1.4868   0.05729   0.05085  -0.0981   0.0026   0.4894
  12.500   1.4790   0.06152   0.05521  -0.0981   0.0025   0.4927
  12.750   1.4704   0.06593   0.05975  -0.0983   0.0025   0.4960
  13.000   1.4618   0.07041   0.06435  -0.0986   0.0025   0.4995
  13.250   1.4532   0.07499   0.06906  -0.0990   0.0024   0.5031
  13.500   1.4459   0.07953   0.07373  -0.0996   0.0024   0.5074
  13.750   1.4384   0.08413   0.07844  -0.1003   0.0023   0.5122
  14.000   1.4322   0.08865   0.08308  -0.1011   0.0023   0.5177
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