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GM15 (smoothed) (gm15sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GM15 (smoothed) (gm15sm-il)
Reynolds number: 1,000,000
Max Cl/Cd: 119.49 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-gm15sm-il-1000000-n5.txt
Download as CSV file: xf-gm15sm-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3610   0.10570   0.10406  -0.0240   1.0000   0.0057
  -9.000  -0.3576   0.10261   0.10098  -0.0247   1.0000   0.0055
  -8.750  -0.3558   0.09955   0.09794  -0.0251   1.0000   0.0052
  -8.500  -0.3444   0.09532   0.09371  -0.0286   0.9992   0.0050
  -8.250  -0.3310   0.09051   0.08889  -0.0332   0.9973   0.0048
  -8.000  -0.3248   0.08655   0.08494  -0.0355   0.9816   0.0048
  -7.750  -0.3110   0.08174   0.08013  -0.0406   0.9731   0.0047
  -7.500  -0.2934   0.07664   0.07503  -0.0471   0.9677   0.0049
  -7.000  -0.1825   0.02015   0.01748  -0.1354   0.9507   0.0056
  -6.750  -0.1497   0.01613   0.01289  -0.1399   0.9461   0.0057
  -6.500  -0.1214   0.01435   0.01080  -0.1411   0.9413   0.0059
  -6.250  -0.0918   0.01320   0.00940  -0.1421   0.9371   0.0061
  -6.000  -0.0635   0.01212   0.00810  -0.1427   0.9333   0.0063
  -5.750  -0.0376   0.01107   0.00681  -0.1426   0.9285   0.0063
  -5.500  -0.0101   0.01024   0.00579  -0.1427   0.9239   0.0064
  -5.250   0.0175   0.00959   0.00498  -0.1428   0.9198   0.0065
  -5.000   0.0437   0.00909   0.00438  -0.1424   0.9146   0.0066
  -4.750   0.0711   0.00867   0.00384  -0.1423   0.9095   0.0067
  -4.500   0.0977   0.00800   0.00300  -0.1421   0.9041   0.0077
  -4.250   0.1246   0.00773   0.00269  -0.1418   0.8977   0.0084
  -4.000   0.1520   0.00752   0.00241  -0.1416   0.8916   0.0092
  -3.750   0.1789   0.00731   0.00214  -0.1412   0.8838   0.0099
  -3.500   0.2059   0.00714   0.00191  -0.1409   0.8753   0.0106
  -3.250   0.2328   0.00693   0.00162  -0.1405   0.8649   0.0127
  -3.000   0.2594   0.00680   0.00146  -0.1401   0.8520   0.0159
  -2.750   0.2857   0.00669   0.00128  -0.1396   0.8359   0.0206
  -2.500   0.3117   0.00662   0.00114  -0.1390   0.8161   0.0251
  -2.250   0.3370   0.00656   0.00101  -0.1383   0.7938   0.0347
  -2.000   0.3618   0.00650   0.00089  -0.1376   0.7687   0.0566
  -1.750   0.3862   0.00642   0.00082  -0.1367   0.7413   0.0950
  -1.500   0.4108   0.00642   0.00077  -0.1359   0.7146   0.1227
  -1.250   0.4358   0.00645   0.00075  -0.1352   0.6903   0.1444
  -1.000   0.4610   0.00648   0.00074  -0.1346   0.6682   0.1689
  -0.750   0.4865   0.00650   0.00075  -0.1340   0.6480   0.1993
  -0.500   0.5120   0.00655   0.00077  -0.1334   0.6296   0.2187
  -0.250   0.5380   0.00660   0.00078  -0.1329   0.6121   0.2329
   0.000   0.5640   0.00667   0.00081  -0.1324   0.5952   0.2462
   0.250   0.5901   0.00673   0.00084  -0.1319   0.5793   0.2588
   0.500   0.6160   0.00681   0.00088  -0.1314   0.5623   0.2725
   0.750   0.6420   0.00689   0.00092  -0.1310   0.5466   0.2858
   1.000   0.6681   0.00697   0.00098  -0.1305   0.5312   0.2993
   1.250   0.6941   0.00705   0.00104  -0.1301   0.5158   0.3133
   1.500   0.7202   0.00713   0.00111  -0.1296   0.5006   0.3270
   1.750   0.7462   0.00722   0.00118  -0.1292   0.4855   0.3421
   2.000   0.7721   0.00732   0.00128  -0.1287   0.4699   0.3575
   2.250   0.7980   0.00742   0.00137  -0.1282   0.4547   0.3756
   2.500   0.8238   0.00753   0.00148  -0.1278   0.4386   0.3940
   2.750   0.8495   0.00764   0.00159  -0.1273   0.4226   0.4151
   3.000   0.8749   0.00776   0.00172  -0.1268   0.4062   0.4426
   3.250   0.9003   0.00787   0.00188  -0.1262   0.3896   0.4778
   3.500   0.9254   0.00794   0.00204  -0.1257   0.3725   0.5366
   4.000   0.9750   0.00816   0.00261  -0.1250   0.2647   1.0000
   4.250   0.9958   0.00885   0.00297  -0.1238   0.1977   1.0000
   4.500   1.0184   0.00937   0.00328  -0.1228   0.1546   1.0000
   4.750   1.0401   0.00999   0.00365  -0.1218   0.1059   1.0000
   5.000   1.0613   0.01067   0.00410  -0.1206   0.0589   1.0000
   5.250   1.0839   0.01120   0.00449  -0.1196   0.0330   1.0000
   5.500   1.1077   0.01158   0.00482  -0.1189   0.0217   1.0000
   5.750   1.1319   0.01191   0.00515  -0.1182   0.0173   1.0000
   6.000   1.1559   0.01226   0.00550  -0.1174   0.0132   1.0000
   6.250   1.1799   0.01259   0.00584  -0.1167   0.0114   1.0000
   6.500   1.2033   0.01298   0.00623  -0.1159   0.0099   1.0000
   6.750   1.2263   0.01342   0.00671  -0.1150   0.0085   1.0000
   7.000   1.2499   0.01375   0.00709  -0.1142   0.0080   1.0000
   7.250   1.2731   0.01413   0.00751  -0.1134   0.0075   1.0000
   7.500   1.2959   0.01453   0.00795  -0.1125   0.0069   1.0000
   7.750   1.3182   0.01497   0.00841  -0.1116   0.0063   1.0000
   8.000   1.3395   0.01552   0.00900  -0.1105   0.0056   1.0000
   8.250   1.3597   0.01616   0.00972  -0.1091   0.0051   1.0000
   8.500   1.3817   0.01656   0.01016  -0.1082   0.0048   1.0000
   8.750   1.4034   0.01699   0.01064  -0.1072   0.0044   1.0000
   9.000   1.4241   0.01749   0.01119  -0.1060   0.0040   1.0000
   9.250   1.4442   0.01802   0.01176  -0.1048   0.0036   1.0000
   9.500   1.4634   0.01861   0.01239  -0.1035   0.0033   1.0000
   9.750   1.4812   0.01931   0.01316  -0.1019   0.0031   1.0000
  10.000   1.4949   0.02036   0.01432  -0.0996   0.0028   1.0000
  10.250   1.5111   0.02109   0.01513  -0.0978   0.0027   1.0000
  10.500   1.5267   0.02182   0.01595  -0.0959   0.0026   1.0000
  10.750   1.5393   0.02266   0.01688  -0.0935   0.0026   1.0000
  11.000   1.5500   0.02347   0.01781  -0.0908   0.0025   1.0000
  11.250   1.5583   0.02442   0.01886  -0.0878   0.0024   1.0000
  11.500   1.5666   0.02538   0.01992  -0.0849   0.0023   1.0000
  11.750   1.5736   0.02643   0.02108  -0.0820   0.0022   1.0000
  12.000   1.5786   0.02766   0.02243  -0.0790   0.0022   1.0000
  12.250   1.5842   0.02890   0.02377  -0.0763   0.0021   1.0000
  12.500   1.5897   0.03019   0.02516  -0.0738   0.0020   1.0000
  12.750   1.5925   0.03177   0.02686  -0.0712   0.0020   1.0000
  13.000   1.5958   0.03336   0.02857  -0.0689   0.0019   1.0000
  13.250   1.5988   0.03507   0.03039  -0.0669   0.0019   1.0000
  13.500   1.5993   0.03710   0.03254  -0.0649   0.0018   1.0000
  13.750   1.6017   0.03904   0.03459  -0.0633   0.0018   1.0000
  14.000   1.6011   0.04140   0.03707  -0.0618   0.0017   1.0000
  14.250   1.5977   0.04424   0.04007  -0.0607   0.0017   1.0000
  14.500   1.5956   0.04708   0.04302  -0.0600   0.0016   1.0000
  14.750   1.5881   0.05079   0.04689  -0.0596   0.0016   1.0000
  15.000   1.5821   0.05456   0.05080  -0.0597   0.0016   1.0000
  15.250   1.5734   0.05894   0.05532  -0.0603   0.0016   1.0000
  15.500   1.5643   0.06363   0.06016  -0.0614   0.0015   1.0000
  15.750   1.5514   0.06922   0.06590  -0.0631   0.0015   1.0000
  16.000   1.5376   0.07526   0.07211  -0.0653   0.0015   1.0000
  16.250   1.5215   0.08207   0.07908  -0.0682   0.0015   1.0000
  16.500   1.5044   0.08942   0.08658  -0.0716   0.0015   1.0000
  16.750   1.4873   0.09709   0.09441  -0.0754   0.0015   1.0000
  17.000   1.4674   0.10576   0.10323  -0.0799   0.0015   1.0000
  17.250   1.4481   0.11457   0.11220  -0.0847   0.0015   1.0000
  17.500   1.4267   0.12427   0.12205  -0.0903   0.0015   1.0000
  17.750   1.4059   0.13415   0.13208  -0.0960   0.0015   1.0000
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