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GEMINI (smoothed) (geminism-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GEMINI (smoothed) (geminism-il)
Reynolds number: 50,000
Max Cl/Cd: 8.88 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-geminism-il-50000.txt
Download as CSV file: xf-geminism-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3722   0.10996   0.10277  -0.0246   1.0000   0.3372
  -9.500  -0.5331   0.08085   0.07410  -0.0526   1.0000   0.1606
  -9.250  -0.5480   0.07670   0.07002  -0.0514   1.0000   0.1578
  -9.000  -0.5923   0.07206   0.06545  -0.0485   1.0000   0.1525
  -8.750  -0.6641   0.06728   0.06045  -0.0430   1.0000   0.1460
  -8.500  -0.6760   0.06401   0.05712  -0.0397   1.0000   0.1446
  -8.250  -0.6913   0.06082   0.05380  -0.0359   1.0000   0.1433
  -8.000  -0.7060   0.05767   0.05045  -0.0320   1.0000   0.1425
  -7.750  -0.7173   0.05462   0.04712  -0.0282   1.0000   0.1423
  -7.500  -0.7246   0.05170   0.04386  -0.0246   1.0000   0.1430
  -7.250  -0.7275   0.04889   0.04065  -0.0213   1.0000   0.1441
  -7.000  -0.7261   0.04617   0.03749  -0.0183   1.0000   0.1453
  -6.750  -0.7207   0.04359   0.03441  -0.0155   1.0000   0.1465
  -6.500  -0.7086   0.04122   0.03187  -0.0137   1.0000   0.1495
  -6.250  -0.6941   0.03965   0.03022  -0.0121   1.0000   0.1553
  -6.000  -0.6806   0.03785   0.02793  -0.0102   1.0000   0.1609
  -5.750  -0.6623   0.03612   0.02615  -0.0090   1.0000   0.1669
  -5.500  -0.6449   0.03479   0.02453  -0.0075   1.0000   0.1761
  -5.250  -0.6265   0.03357   0.02336  -0.0064   1.0000   0.1876
  -5.000  -0.6071   0.03234   0.02210  -0.0052   1.0000   0.2013
  -4.750  -0.5887   0.03127   0.02101  -0.0039   1.0000   0.2223
  -4.500  -0.5704   0.03012   0.02007  -0.0026   1.0000   0.2529
  -4.250  -0.5538   0.02872   0.01920  -0.0010   1.0000   0.3113
  -4.000  -0.5418   0.02730   0.01872   0.0019   1.0000   0.4300
  -3.750  -0.5329   0.02697   0.01894   0.0058   1.0000   0.5298
  -3.500  -0.5225   0.02707   0.01936   0.0098   1.0000   0.6043
  -3.250  -0.5114   0.02730   0.01978   0.0138   1.0000   0.6691
  -3.000  -0.5004   0.02763   0.02025   0.0182   1.0000   0.7298
  -2.750  -0.4900   0.02816   0.02090   0.0233   1.0000   0.7928
  -2.500  -0.4689   0.02912   0.02189   0.0273   1.0000   0.8596
  -2.250  -0.3578   0.03194   0.02421   0.0140   0.9939   0.9264
  -2.000  -0.1910   0.03446   0.02601  -0.0126   0.9847   0.9677
  -1.750  -0.0518   0.03535   0.02639  -0.0361   0.9766   1.0000
  -1.500  -0.0206   0.03514   0.02600  -0.0405   0.9620   1.0000
  -1.250   0.0077   0.03504   0.02575  -0.0439   0.9479   1.0000
  -1.000   0.0326   0.03503   0.02559  -0.0463   0.9340   1.0000
  -0.750   0.0536   0.03512   0.02554  -0.0478   0.9202   1.0000
  -0.500   0.0728   0.03527   0.02557  -0.0485   0.9066   1.0000
  -0.250   0.0927   0.03552   0.02569  -0.0491   0.8936   1.0000
   0.000   0.1216   0.03584   0.02588  -0.0509   0.8813   1.0000
   0.250   0.1380   0.03622   0.02614  -0.0504   0.8682   1.0000
   0.500   0.1481   0.03671   0.02653  -0.0488   0.8549   1.0000
   0.750   0.1634   0.03729   0.02699  -0.0479   0.8422   1.0000
   1.000   0.1885   0.03790   0.02749  -0.0484   0.8306   1.0000
   1.250   0.2225   0.03844   0.02794  -0.0502   0.8194   1.0000
   1.500   0.2275   0.03928   0.02869  -0.0476   0.8065   1.0000
   1.750   0.2419   0.04012   0.02944  -0.0463   0.7946   1.0000
   2.000   0.2750   0.04076   0.03002  -0.0477   0.7841   1.0000
   2.250   0.2909   0.04164   0.03084  -0.0466   0.7726   1.0000
   2.500   0.2983   0.04273   0.03187  -0.0445   0.7607   1.0000
   2.750   0.3229   0.04359   0.03269  -0.0446   0.7504   1.0000
   3.000   0.3477   0.04442   0.03349  -0.0447   0.7399   1.0000
   3.250   0.3505   0.04579   0.03482  -0.0422   0.7284   1.0000
   3.500   0.3743   0.04677   0.03578  -0.0422   0.7186   1.0000
   3.750   0.3954   0.04777   0.03678  -0.0419   0.7082   1.0000
   4.000   0.3972   0.04941   0.03839  -0.0396   0.6974   1.0000
   4.250   0.4295   0.05021   0.03922  -0.0405   0.6883   1.0000
   4.500   0.4343   0.05183   0.04083  -0.0386   0.6775   1.0000
   4.750   0.4411   0.05354   0.04254  -0.0371   0.6677   1.0000
   5.000   0.4802   0.05410   0.04316  -0.0384   0.6586   1.0000
   5.250   0.4679   0.05659   0.04562  -0.0355   0.6481   1.0000
   5.500   0.4891   0.05792   0.04700  -0.0354   0.6390   1.0000
   5.750   0.5009   0.05960   0.04871  -0.0345   0.6292   1.0000
   6.000   0.5034   0.06179   0.05092  -0.0332   0.6201   1.0000
   6.250   0.5405   0.06250   0.05173  -0.0340   0.6108   1.0000
   6.500   0.5228   0.06569   0.05491  -0.0317   0.6018   1.0000
   6.750   0.5523   0.06684   0.05614  -0.0320   0.5927   1.0000
   7.000   0.5424   0.06984   0.05916  -0.0305   0.5845   1.0000
   7.250   0.5617   0.07157   0.06096  -0.0304   0.5756   1.0000
   7.500   0.5587   0.07443   0.06386  -0.0295   0.5682   1.0000
   7.750   0.5751   0.07641   0.06592  -0.0293   0.5595   1.0000
   8.000   0.5684   0.07969   0.06925  -0.0286   0.5541   1.0000
   8.250   0.5925   0.08141   0.07106  -0.0287   0.5448   1.0000
   8.500   0.5802   0.08519   0.07487  -0.0282   0.5417   1.0000
   8.750   0.5763   0.08884   0.07858  -0.0283   0.5411   1.0000
   9.000   0.5756   0.09260   0.08240  -0.0287   0.5428   1.0000
   9.250   0.5910   0.09650   0.08642  -0.0302   0.5471   1.0000
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