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GEMINI (smoothed) (geminism-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GEMINI (smoothed) (geminism-il)
Reynolds number: 100,000
Max Cl/Cd: 47.28 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-geminism-il-100000.txt
Download as CSV file: xf-geminism-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GEMINI (smoothed)                               
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.4029   0.10952   0.10435  -0.0368   1.0000   0.1689
 -10.500  -0.5807   0.07263   0.06762  -0.0655   1.0000   0.0922
 -10.250  -0.6141   0.06772   0.06262  -0.0644   1.0000   0.0873
 -10.000  -0.6415   0.06461   0.05950  -0.0606   1.0000   0.0859
  -9.750  -0.6726   0.06148   0.05630  -0.0558   1.0000   0.0843
  -9.500  -0.7082   0.05812   0.05277  -0.0500   1.0000   0.0822
  -9.250  -0.7778   0.05477   0.04861  -0.0389   1.0000   0.0773
  -9.000  -0.7875   0.05315   0.04672  -0.0342   1.0000   0.0768
  -8.750  -0.7957   0.05035   0.04368  -0.0301   1.0000   0.0769
  -8.500  -0.8008   0.04705   0.04016  -0.0265   1.0000   0.0774
  -8.250  -0.8002   0.04423   0.03717  -0.0235   1.0000   0.0784
  -8.000  -0.7962   0.04198   0.03474  -0.0207   1.0000   0.0793
  -7.750  -0.7904   0.03983   0.03233  -0.0180   1.0000   0.0799
  -7.500  -0.7818   0.03786   0.03011  -0.0155   1.0000   0.0807
  -7.250  -0.7703   0.03630   0.02834  -0.0135   1.0000   0.0826
  -7.000  -0.7556   0.03483   0.02661  -0.0120   0.9995   0.0853
  -6.750  -0.7181   0.03292   0.02418  -0.0143   0.9940   0.0885
  -6.500  -0.6805   0.03074   0.02174  -0.0166   0.9886   0.0918
  -6.250  -0.6425   0.02937   0.02035  -0.0193   0.9823   0.0981
  -6.000  -0.6027   0.02826   0.01893  -0.0217   0.9762   0.1038
  -5.750  -0.5648   0.02678   0.01765  -0.0242   0.9701   0.1124
  -5.500  -0.5302   0.02569   0.01657  -0.0259   0.9629   0.1226
  -5.250  -0.4912   0.02464   0.01565  -0.0285   0.9569   0.1386
  -5.000  -0.4629   0.02375   0.01491  -0.0290   0.9479   0.1637
  -4.750  -0.4324   0.02236   0.01411  -0.0302   0.9412   0.2395
  -4.500  -0.4101   0.02122   0.01368  -0.0298   0.9321   0.3584
  -4.250  -0.3844   0.02079   0.01361  -0.0296   0.9233   0.4433
  -4.000  -0.3513   0.02053   0.01359  -0.0304   0.9157   0.5176
  -3.750  -0.3276   0.02048   0.01367  -0.0294   0.9059   0.5733
  -3.500  -0.2898   0.02039   0.01369  -0.0306   0.8997   0.6303
  -3.250  -0.2683   0.02048   0.01385  -0.0288   0.8893   0.6748
  -3.000  -0.2286   0.02051   0.01396  -0.0297   0.8840   0.7266
  -2.750  -0.2051   0.02069   0.01419  -0.0279   0.8740   0.7615
  -2.500  -0.1603   0.02063   0.01407  -0.0300   0.8689   0.7927
  -2.250  -0.1287   0.02078   0.01418  -0.0299   0.8600   0.8169
  -2.000  -0.0854   0.02074   0.01405  -0.0318   0.8540   0.8418
  -1.750  -0.0343   0.02078   0.01398  -0.0352   0.8486   0.8614
  -1.500   0.0104   0.02093   0.01404  -0.0378   0.8401   0.8795
  -1.250   0.0739   0.02082   0.01378  -0.0436   0.8359   0.8945
  -1.000   0.1239   0.02098   0.01385  -0.0474   0.8267   0.9097
  -0.750   0.1907   0.02084   0.01357  -0.0540   0.8209   0.9232
  -0.500   0.2500   0.02085   0.01349  -0.0598   0.8119   0.9367
  -0.250   0.3136   0.02055   0.01307  -0.0663   0.8043   0.9471
   0.000   0.3625   0.02043   0.01289  -0.0707   0.7931   0.9594
   0.250   0.4147   0.02010   0.01246  -0.0755   0.7841   0.9704
   0.500   0.4639   0.01985   0.01215  -0.0801   0.7727   0.9817
   0.750   0.5127   0.01962   0.01187  -0.0848   0.7607   0.9929
   1.000   0.5556   0.01931   0.01150  -0.0884   0.7497   1.0000
   1.250   0.5746   0.01917   0.01128  -0.0873   0.7392   1.0000
   1.500   0.5900   0.01921   0.01130  -0.0857   0.7268   1.0000
   1.750   0.6073   0.01922   0.01127  -0.0843   0.7156   1.0000
   2.000   0.6292   0.01908   0.01106  -0.0834   0.7064   1.0000
   2.250   0.6445   0.01922   0.01120  -0.0816   0.6941   1.0000
   2.500   0.6620   0.01932   0.01128  -0.0801   0.6832   1.0000
   2.750   0.6852   0.01925   0.01113  -0.0792   0.6744   1.0000
   3.000   0.6999   0.01949   0.01139  -0.0772   0.6624   1.0000
   3.250   0.7179   0.01967   0.01156  -0.0756   0.6521   1.0000
   3.500   0.7413   0.01968   0.01149  -0.0747   0.6430   1.0000
   3.750   0.7562   0.01999   0.01185  -0.0726   0.6316   1.0000
   4.000   0.7765   0.02016   0.01201  -0.0712   0.6221   1.0000
   4.250   0.7980   0.02029   0.01211  -0.0700   0.6123   1.0000
   4.500   0.8140   0.02065   0.01251  -0.0680   0.6017   1.0000
   4.750   0.8393   0.02073   0.01254  -0.0674   0.5932   1.0000
   5.000   0.8556   0.02108   0.01295  -0.0654   0.5824   1.0000
   5.250   0.8743   0.02141   0.01331  -0.0638   0.5726   1.0000
   5.500   0.8999   0.02152   0.01339  -0.0632   0.5637   1.0000
   5.750   0.9147   0.02200   0.01396  -0.0609   0.5531   1.0000
   6.000   0.9385   0.02223   0.01417  -0.0601   0.5442   1.0000
   6.250   0.9582   0.02257   0.01456  -0.0586   0.5342   1.0000
   6.500   0.9759   0.02303   0.01511  -0.0569   0.5244   1.0000
   6.750   1.0041   0.02316   0.01520  -0.0567   0.5159   1.0000
   7.000   1.0172   0.02374   0.01593  -0.0542   0.5051   1.0000
   7.250   1.0380   0.02397   0.01618  -0.0528   0.4939   1.0000
   7.500   1.0613   0.02392   0.01611  -0.0516   0.4809   1.0000
   7.750   1.0828   0.02384   0.01599  -0.0500   0.4665   1.0000
   8.000   1.1030   0.02385   0.01599  -0.0483   0.4525   1.0000
   8.250   1.1164   0.02412   0.01635  -0.0457   0.4392   1.0000
   8.500   1.1311   0.02430   0.01662  -0.0432   0.4252   1.0000
   8.750   1.1452   0.02442   0.01679  -0.0406   0.4106   1.0000
   9.000   1.1580   0.02458   0.01701  -0.0378   0.3960   1.0000
   9.250   1.1678   0.02470   0.01718  -0.0345   0.3797   1.0000
   9.500   1.1746   0.02486   0.01740  -0.0307   0.3627   1.0000
   9.750   1.1762   0.02504   0.01758  -0.0261   0.3424   1.0000
  10.000   1.1691   0.02549   0.01812  -0.0203   0.3188   1.0000
  10.250   1.1590   0.02619   0.01879  -0.0144   0.2913   1.0000
  10.500   1.1449   0.02749   0.01993  -0.0088   0.2518   1.0000
  10.750   1.1258   0.02972   0.02182  -0.0039   0.1953   1.0000
  11.000   1.1033   0.03285   0.02451   0.0002   0.1407   1.0000
  11.250   1.0839   0.03628   0.02763   0.0032   0.1105   1.0000
  11.500   1.0699   0.03961   0.03082   0.0053   0.0966   1.0000
  11.750   1.0591   0.04287   0.03405   0.0068   0.0884   1.0000
  12.000   1.0502   0.04611   0.03731   0.0080   0.0828   1.0000
  12.250   1.0434   0.04927   0.04051   0.0090   0.0781   1.0000
  12.500   1.0349   0.05256   0.04378   0.0099   0.0748   1.0000
  12.750   1.0357   0.05497   0.04626   0.0110   0.0716   1.0000
  13.000   1.0393   0.05709   0.04841   0.0121   0.0682   1.0000
  13.250   1.0471   0.05862   0.04983   0.0137   0.0646   1.0000
  13.500   1.0649   0.05938   0.05055   0.0157   0.0612   1.0000
  13.750   1.0845   0.06030   0.05153   0.0172   0.0586   1.0000
  14.000   1.1108   0.06100   0.05222   0.0189   0.0563   1.0000
  14.250   1.1747   0.06137   0.05238   0.0204   0.0528   1.0000
  14.500   1.1756   0.06391   0.05520   0.0213   0.0520   1.0000
  14.750   1.1774   0.06668   0.05823   0.0220   0.0511   1.0000
  15.000   1.1794   0.06971   0.06151   0.0227   0.0506   1.0000
  15.250   1.1786   0.07309   0.06515   0.0232   0.0503   1.0000
  15.500   1.1731   0.07686   0.06918   0.0235   0.0503   1.0000
  15.750   1.1637   0.08099   0.07358   0.0235   0.0503   1.0000
  16.000   1.1507   0.08551   0.07835   0.0231   0.0505   1.0000
  16.250   1.1349   0.09045   0.08354   0.0222   0.0507   1.0000
  16.500   1.1169   0.09585   0.08916   0.0208   0.0510   1.0000
  16.750   1.0972   0.10170   0.09524   0.0189   0.0513   1.0000
  17.000   1.0767   0.10805   0.10179   0.0164   0.0517   1.0000
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