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GM15 (smoothed) (gm15sm-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GM15 (smoothed) (gm15sm-il)
Reynolds number: 500,000
Max Cl/Cd: 123.6 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-gm15sm-il-500000.txt
Download as CSV file: xf-gm15sm-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3535   0.09508   0.09295  -0.0239   1.0000   0.0164
  -7.500  -0.3624   0.09354   0.09145  -0.0215   1.0000   0.0164
  -7.250  -0.3728   0.09209   0.09005  -0.0188   1.0000   0.0164
  -7.000  -0.3528   0.08758   0.08554  -0.0248   0.9970   0.0165
  -6.750  -0.3280   0.08238   0.08032  -0.0322   0.9937   0.0165
  -6.500  -0.3138   0.07425   0.07222  -0.0407   0.9894   0.0174
  -6.250  -0.2889   0.07080   0.06875  -0.0455   0.9869   0.0181
  -6.000  -0.2638   0.06729   0.06522  -0.0508   0.9836   0.0192
  -5.750  -0.2342   0.06279   0.06070  -0.0585   0.9795   0.0206
  -5.500  -0.1920   0.05657   0.05443  -0.0708   0.9767   0.0233
  -5.250  -0.1344   0.04954   0.04730  -0.0862   0.9749   0.0250
  -5.000  -0.0792   0.03200   0.02930  -0.1106   0.9697   0.0268
  -4.750  -0.0438   0.02926   0.02644  -0.1149   0.9673   0.0281
  -4.500  -0.0021   0.02502   0.02185  -0.1210   0.9655   0.0299
  -4.250   0.0464   0.01588   0.01122  -0.1267   0.9642   0.0170
  -4.000   0.0841   0.01415   0.00920  -0.1289   0.9631   0.0168
  -3.750   0.1216   0.01164   0.00632  -0.1312   0.9621   0.0177
  -3.500   0.1525   0.01070   0.00527  -0.1318   0.9579   0.0196
  -3.250   0.1881   0.01004   0.00453  -0.1333   0.9549   0.0217
  -3.000   0.2258   0.00973   0.00415  -0.1352   0.9522   0.0251
  -2.750   0.2639   0.00876   0.00307  -0.1373   0.9496   0.0339
  -2.500   0.2954   0.00829   0.00258  -0.1379   0.9442   0.0528
  -2.250   0.3277   0.00772   0.00231  -0.1389   0.9385   0.1412
  -2.000   0.3603   0.00752   0.00219  -0.1398   0.9329   0.1876
  -1.750   0.3884   0.00742   0.00210  -0.1396   0.9249   0.2135
  -1.500   0.4172   0.00732   0.00204  -0.1396   0.9174   0.2385
  -1.250   0.4454   0.00722   0.00197  -0.1395   0.9091   0.2632
  -1.000   0.4717   0.00715   0.00190  -0.1388   0.8992   0.2847
  -0.750   0.4989   0.00706   0.00182  -0.1384   0.8889   0.3025
  -0.500   0.5261   0.00697   0.00174  -0.1380   0.8773   0.3200
  -0.250   0.5528   0.00690   0.00167  -0.1375   0.8638   0.3378
   0.000   0.5791   0.00683   0.00160  -0.1369   0.8478   0.3560
   0.250   0.6056   0.00679   0.00155  -0.1363   0.8292   0.3760
   0.500   0.6319   0.00678   0.00151  -0.1357   0.8083   0.3976
   0.750   0.6576   0.00680   0.00150  -0.1350   0.7845   0.4224
   1.250   0.7072   0.00688   0.00157  -0.1333   0.7341   0.4936
   1.500   0.7307   0.00682   0.00166  -0.1323   0.7107   0.5815
   2.000   0.7872   0.00642   0.00182  -0.1323   0.6667   1.0000
   2.250   0.8121   0.00661   0.00191  -0.1315   0.6467   1.0000
   2.500   0.8370   0.00681   0.00202  -0.1308   0.6279   1.0000
   2.750   0.8621   0.00699   0.00213  -0.1301   0.6090   1.0000
   3.000   0.8870   0.00719   0.00228  -0.1293   0.5907   1.0000
   3.250   0.9119   0.00739   0.00242  -0.1286   0.5726   1.0000
   3.500   0.9369   0.00758   0.00256  -0.1279   0.5538   1.0000
   3.750   0.9617   0.00780   0.00273  -0.1272   0.5348   1.0000
   4.000   0.9862   0.00803   0.00290  -0.1264   0.5144   1.0000
   4.250   1.0088   0.00836   0.00311  -0.1253   0.4772   1.0000
   4.500   1.0305   0.00879   0.00333  -0.1240   0.4289   1.0000
   4.750   1.0523   0.00925   0.00359  -0.1229   0.3819   1.0000
   5.000   1.0740   0.00978   0.00389  -0.1217   0.3357   1.0000
   5.250   1.0958   0.01032   0.00423  -0.1207   0.2895   1.0000
   5.500   1.1164   0.01101   0.00468  -0.1194   0.2332   1.0000
   5.750   1.1324   0.01225   0.00537  -0.1176   0.1347   1.0000
   6.000   1.1434   0.01417   0.00663  -0.1149   0.0315   1.0000
   6.250   1.1649   0.01486   0.00736  -0.1136   0.0248   1.0000
   6.500   1.1844   0.01576   0.00836  -0.1120   0.0209   1.0000
   6.750   1.2056   0.01642   0.00912  -0.1107   0.0194   1.0000
   7.000   1.2254   0.01720   0.00998  -0.1092   0.0178   1.0000
   7.250   1.2448   0.01798   0.01084  -0.1077   0.0161   1.0000
   7.500   1.2538   0.01996   0.01297  -0.1045   0.0139   1.0000
   7.750   1.2719   0.02090   0.01400  -0.1028   0.0133   1.0000
   8.000   1.2896   0.02191   0.01511  -0.1010   0.0125   1.0000
   8.250   1.3063   0.02310   0.01640  -0.0991   0.0117   1.0000
   8.500   1.3226   0.02446   0.01786  -0.0971   0.0110   1.0000
   8.750   1.3389   0.02583   0.01934  -0.0953   0.0104   1.0000
   9.000   1.3547   0.02705   0.02063  -0.0936   0.0097   1.0000
   9.250   1.3678   0.02984   0.02356  -0.0917   0.0089   1.0000
   9.500   1.3808   0.03364   0.02768  -0.0898   0.0085   1.0000
   9.750   1.3935   0.03546   0.02972  -0.0876   0.0083   1.0000
  10.000   1.4035   0.03760   0.03211  -0.0852   0.0082   1.0000
  10.250   1.4096   0.04025   0.03504  -0.0823   0.0080   1.0000
  10.500   1.4094   0.04298   0.03804  -0.0787   0.0079   1.0000
  10.750   1.4033   0.04596   0.04129  -0.0745   0.0079   1.0000
  11.000   1.3932   0.04910   0.04469  -0.0704   0.0079   1.0000
  11.250   1.3791   0.05265   0.04849  -0.0667   0.0079   1.0000
  11.500   1.3629   0.05645   0.05255  -0.0636   0.0079   1.0000
  11.750   1.3444   0.06072   0.05704  -0.0615   0.0080   1.0000
  12.000   1.3238   0.06562   0.06215  -0.0604   0.0081   1.0000
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