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GM15 (smoothed) (gm15sm-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GM15 (smoothed) (gm15sm-il)
Reynolds number: 200,000
Max Cl/Cd: 91.52 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-gm15sm-il-200000.txt
Download as CSV file: xf-gm15sm-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GM15 (smoothed)                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3535   0.09956   0.09621  -0.0283   1.0000   0.0359
  -7.500  -0.3635   0.09830   0.09503  -0.0262   1.0000   0.0360
  -7.250  -0.3686   0.09644   0.09322  -0.0254   1.0000   0.0361
  -7.000  -0.3701   0.09412   0.09096  -0.0255   1.0000   0.0362
  -6.750  -0.3699   0.09154   0.08841  -0.0262   1.0000   0.0362
  -6.500  -0.3764   0.08628   0.08322  -0.0219   1.0000   0.0376
  -6.250  -0.3737   0.08426   0.08122  -0.0190   1.0000   0.0389
  -6.000  -0.3716   0.08237   0.07936  -0.0176   1.0000   0.0412
  -5.750  -0.3696   0.07996   0.07698  -0.0181   1.0000   0.0429
  -5.500  -0.3644   0.07712   0.07417  -0.0205   1.0000   0.0455
  -5.250  -0.3343   0.07237   0.06938  -0.0355   1.0000   0.0484
  -5.000  -0.3138   0.06568   0.06267  -0.0425   0.9989   0.0494
  -4.750  -0.2943   0.06280   0.05980  -0.0420   0.9955   0.0512
  -4.500  -0.2606   0.05920   0.05616  -0.0472   0.9912   0.0544
  -4.250  -0.1850   0.04861   0.04525  -0.0708   0.9878   0.0632
  -4.000  -0.1570   0.04667   0.04331  -0.0720   0.9836   0.0659
  -3.750  -0.0957   0.03882   0.03508  -0.0867   0.9803   0.0775
  -3.500  -0.0228   0.02377   0.01823  -0.1000   0.9825   0.0353
  -3.250   0.0181   0.02046   0.01428  -0.1031   0.9798   0.0347
  -3.000   0.0585   0.01824   0.01155  -0.1058   0.9770   0.0386
  -2.750   0.0990   0.01680   0.00988  -0.1082   0.9740   0.0410
  -2.500   0.1347   0.01572   0.00863  -0.1094   0.9682   0.0456
  -2.250   0.1753   0.01470   0.00756  -0.1119   0.9643   0.0563
  -2.000   0.2162   0.01383   0.00672  -0.1144   0.9603   0.0868
  -1.750   0.2526   0.01314   0.00644  -0.1162   0.9536   0.2054
  -1.500   0.2963   0.01303   0.00632  -0.1193   0.9495   0.2574
  -1.250   0.3321   0.01295   0.00626  -0.1208   0.9419   0.2923
  -1.000   0.3751   0.01274   0.00604  -0.1236   0.9373   0.3251
  -0.750   0.4165   0.01246   0.00578  -0.1261   0.9320   0.3518
  -0.500   0.4558   0.01216   0.00555  -0.1282   0.9251   0.3774
  -0.250   0.5006   0.01178   0.00523  -0.1313   0.9211   0.4065
   0.000   0.5318   0.01151   0.00505  -0.1316   0.9103   0.4330
   0.250   0.5648   0.01119   0.00483  -0.1323   0.9002   0.4648
   0.500   0.5993   0.01078   0.00458  -0.1332   0.8906   0.5059
   0.750   0.6309   0.01025   0.00434  -0.1335   0.8797   0.5794
   1.000   0.6678   0.00930   0.00406  -0.1347   0.8667   1.0000
   1.250   0.6972   0.00921   0.00387  -0.1345   0.8511   1.0000
   1.500   0.7250   0.00916   0.00374  -0.1340   0.8327   1.0000
   1.750   0.7541   0.00912   0.00361  -0.1337   0.8140   1.0000
   2.000   0.7825   0.00914   0.00356  -0.1334   0.7936   1.0000
   2.250   0.8103   0.00921   0.00353  -0.1329   0.7719   1.0000
   2.500   0.8370   0.00935   0.00356  -0.1323   0.7494   1.0000
   2.750   0.8637   0.00953   0.00363  -0.1316   0.7276   1.0000
   3.000   0.8889   0.00975   0.00380  -0.1308   0.7048   1.0000
   3.250   0.9143   0.01000   0.00396  -0.1300   0.6835   1.0000
   3.500   0.9390   0.01026   0.00416  -0.1291   0.6616   1.0000
   3.750   0.9636   0.01054   0.00438  -0.1282   0.6408   1.0000
   4.000   0.9879   0.01082   0.00463  -0.1272   0.6195   1.0000
   4.250   1.0121   0.01112   0.00494  -0.1263   0.5984   1.0000
   4.500   1.0359   0.01143   0.00523  -0.1253   0.5766   1.0000
   4.750   1.0587   0.01173   0.00551  -0.1240   0.5507   1.0000
   5.000   1.0786   0.01206   0.00570  -0.1221   0.5097   1.0000
   5.250   1.0975   0.01249   0.00594  -0.1202   0.4622   1.0000
   5.500   1.1174   0.01296   0.00627  -0.1186   0.4186   1.0000
   5.750   1.1365   0.01353   0.00672  -0.1169   0.3680   1.0000
   6.000   1.1526   0.01441   0.00726  -0.1147   0.2945   1.0000
   6.250   1.1529   0.01727   0.00869  -0.1108   0.0847   1.0000
   6.500   1.1653   0.01913   0.01032  -0.1081   0.0474   1.0000
   6.750   1.1800   0.02058   0.01185  -0.1057   0.0406   1.0000
   7.000   1.1959   0.02182   0.01320  -0.1035   0.0367   1.0000
   7.250   1.2089   0.02342   0.01482  -0.1011   0.0327   1.0000
   7.500   1.2228   0.02533   0.01684  -0.0987   0.0304   1.0000
   7.750   1.2416   0.02694   0.01857  -0.0970   0.0290   1.0000
   8.000   1.2624   0.02890   0.02065  -0.0956   0.0277   1.0000
   8.250   1.2829   0.03064   0.02252  -0.0943   0.0255   1.0000
   8.500   1.3018   0.03268   0.02460  -0.0932   0.0231   1.0000
   8.750   1.3251   0.03638   0.02852  -0.0925   0.0223   1.0000
   9.000   1.3449   0.04002   0.03248  -0.0912   0.0222   1.0000
   9.250   1.3610   0.04294   0.03575  -0.0892   0.0225   1.0000
   9.500   1.3690   0.04756   0.04124  -0.0850   0.0257   1.0000
   9.750   1.3688   0.05407   0.04828  -0.0816   0.0293   1.0000
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