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GM15 (smoothed) (gm15sm-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GM15 (smoothed) (gm15sm-il)
Reynolds number: 50,000
Max Cl/Cd: 46.07 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-gm15sm-il-50000-n5.txt
Download as CSV file: xf-gm15sm-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3455   0.10305   0.09633  -0.0270   1.0000   0.1008
  -7.250  -0.3557   0.10209   0.09553  -0.0271   1.0000   0.1017
  -7.000  -0.3591   0.10032   0.09388  -0.0287   1.0000   0.1021
  -6.750  -0.3487   0.09569   0.08928  -0.0253   1.0000   0.1045
  -6.500  -0.3441   0.09297   0.08661  -0.0237   1.0000   0.1085
  -6.250  -0.3446   0.09085   0.08458  -0.0241   1.0000   0.1121
  -5.750  -0.3355   0.08069   0.07448  -0.0353   1.0000   0.0625
  -5.500  -0.3295   0.07792   0.07171  -0.0330   1.0000   0.0594
  -5.250  -0.3215   0.07459   0.06842  -0.0341   1.0000   0.0574
  -5.000  -0.3097   0.07064   0.06448  -0.0371   1.0000   0.0548
  -4.750  -0.2703   0.06122   0.05482  -0.0532   1.0000   0.0486
  -4.500  -0.2520   0.05724   0.05080  -0.0557   1.0000   0.0481
  -4.250  -0.2252   0.05220   0.04561  -0.0609   1.0000   0.0474
  -4.000  -0.1882   0.04598   0.03908  -0.0688   1.0000   0.0469
  -3.750  -0.1434   0.03942   0.03192  -0.0778   1.0000   0.0468
  -3.500  -0.0970   0.03378   0.02524  -0.0851   1.0000   0.0484
  -3.250  -0.0697   0.03165   0.02295  -0.0868   1.0000   0.0532
  -3.000  -0.0365   0.02904   0.01973  -0.0889   1.0000   0.0572
  -2.750  -0.0040   0.02678   0.01678  -0.0902   1.0000   0.0606
  -2.500   0.0224   0.02547   0.01530  -0.0905   1.0000   0.0678
  -2.250   0.0487   0.02444   0.01402  -0.0906   1.0000   0.0789
  -2.000   0.0764   0.02347   0.01275  -0.0907   1.0000   0.0916
  -1.750   0.1099   0.02281   0.01202  -0.0923   0.9974   0.1287
  -1.500   0.1512   0.02247   0.01187  -0.0954   0.9896   0.2121
  -1.250   0.1895   0.02270   0.01213  -0.0979   0.9803   0.2853
  -1.000   0.2283   0.02275   0.01205  -0.1002   0.9714   0.3338
  -0.750   0.2686   0.02269   0.01186  -0.1028   0.9627   0.3727
  -0.500   0.3064   0.02258   0.01166  -0.1050   0.9527   0.4081
  -0.250   0.3450   0.02243   0.01149  -0.1072   0.9430   0.4434
   0.000   0.3863   0.02222   0.01129  -0.1099   0.9342   0.4845
   0.250   0.4226   0.02196   0.01116  -0.1116   0.9230   0.5333
   0.500   0.4569   0.02145   0.01105  -0.1128   0.9117   0.6183
   0.750   0.4886   0.02083   0.01078  -0.1132   0.8983   1.0000
   1.000   0.5256   0.02097   0.01070  -0.1149   0.8858   1.0000
   1.250   0.5621   0.02108   0.01065  -0.1164   0.8730   1.0000
   1.500   0.5977   0.02116   0.01065  -0.1177   0.8599   1.0000
   1.750   0.6317   0.02121   0.01063  -0.1185   0.8461   1.0000
   2.000   0.6650   0.02124   0.01062  -0.1191   0.8319   1.0000
   2.250   0.6979   0.02125   0.01062  -0.1196   0.8173   1.0000
   2.500   0.7305   0.02125   0.01067  -0.1199   0.8022   1.0000
   2.750   0.7632   0.02122   0.01066  -0.1202   0.7867   1.0000
   3.000   0.7961   0.02118   0.01066  -0.1204   0.7709   1.0000
   3.250   0.8277   0.02119   0.01072  -0.1204   0.7540   1.0000
   3.500   0.8570   0.02128   0.01094  -0.1200   0.7352   1.0000
   3.750   0.8880   0.02134   0.01107  -0.1198   0.7168   1.0000
   4.000   0.9181   0.02145   0.01125  -0.1195   0.6977   1.0000
   4.250   0.9459   0.02168   0.01156  -0.1188   0.6769   1.0000
   4.500   0.9749   0.02189   0.01184  -0.1183   0.6567   1.0000
   4.750   1.0007   0.02224   0.01240  -0.1174   0.6347   1.0000
   5.000   1.0276   0.02258   0.01286  -0.1166   0.6132   1.0000
   5.250   1.0527   0.02301   0.01344  -0.1155   0.5907   1.0000
   5.500   1.0773   0.02347   0.01407  -0.1145   0.5681   1.0000
   5.750   1.1025   0.02393   0.01468  -0.1134   0.5456   1.0000
   6.000   1.1251   0.02448   0.01554  -0.1120   0.5210   1.0000
   6.250   1.1438   0.02490   0.01606  -0.1096   0.4854   1.0000
   6.500   1.1511   0.02531   0.01617  -0.1051   0.4169   1.0000
   6.750   1.1577   0.02623   0.01669  -0.1013   0.3375   1.0000
   7.000   1.1648   0.02770   0.01772  -0.0981   0.2447   1.0000
   7.250   1.1664   0.03049   0.01957  -0.0950   0.1237   1.0000
   7.500   1.1713   0.03339   0.02199  -0.0923   0.0826   1.0000
   7.750   1.1782   0.03580   0.02430  -0.0898   0.0671   1.0000
   8.000   1.1870   0.03788   0.02664  -0.0873   0.0597   1.0000
   8.250   1.1936   0.04013   0.02897  -0.0846   0.0550   1.0000
   8.500   1.2039   0.04219   0.03126  -0.0822   0.0502   1.0000
   8.750   1.2141   0.04426   0.03347  -0.0800   0.0452   1.0000
   9.000   1.2290   0.04689   0.03613  -0.0784   0.0419   1.0000
   9.250   1.2562   0.04959   0.03922  -0.0776   0.0397   1.0000
   9.500   1.2811   0.05282   0.04284  -0.0768   0.0379   1.0000
   9.750   1.2972   0.05614   0.04654  -0.0755   0.0363   1.0000
  10.000   1.3050   0.05923   0.04994  -0.0736   0.0343   1.0000
  10.250   1.3083   0.06242   0.05331  -0.0717   0.0326   1.0000
  10.500   1.3099   0.06681   0.05794  -0.0701   0.0313   1.0000
  10.750   1.3008   0.07005   0.06159  -0.0672   0.0309   1.0000
  11.000   1.2900   0.07374   0.06565  -0.0650   0.0307   1.0000
  11.250   1.2773   0.07782   0.07005  -0.0634   0.0306   1.0000
  11.500   1.2625   0.08225   0.07478  -0.0626   0.0306   1.0000
  11.750   1.2462   0.08709   0.07988  -0.0627   0.0306   1.0000
  12.000   1.2288   0.09241   0.08544  -0.0637   0.0306   1.0000
  12.250   1.2110   0.09825   0.09150  -0.0658   0.0307   1.0000
  12.500   1.1929   0.10465   0.09808  -0.0688   0.0309   1.0000
  12.750   1.1753   0.11157   0.10516  -0.0726   0.0310   1.0000
  13.000   1.1587   0.11896   0.11268  -0.0770   0.0312   1.0000
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