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GM15 (smoothed) (gm15sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GM15 (smoothed) (gm15sm-il)
Reynolds number: 1,000,000
Max Cl/Cd: 146.49 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-gm15sm-il-1000000.txt
Download as CSV file: xf-gm15sm-il-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3490   0.10134   0.09972  -0.0251   1.0000   0.0100
  -8.500  -0.3483   0.09879   0.09720  -0.0250   1.0000   0.0101
  -8.250  -0.3546   0.09702   0.09546  -0.0233   1.0000   0.0104
  -8.000  -0.3423   0.09346   0.09191  -0.0266   0.9991   0.0105
  -7.750  -0.3254   0.08927   0.08772  -0.0313   0.9973   0.0106
  -7.500  -0.3093   0.08505   0.08351  -0.0361   0.9947   0.0106
  -7.250  -0.2954   0.08104   0.07950  -0.0403   0.9903   0.0106
  -7.000  -0.2751   0.07635   0.07481  -0.0465   0.9858   0.0106
  -6.750  -0.2563   0.07175   0.07021  -0.0523   0.9806   0.0107
  -6.500  -0.2309   0.06593   0.06438  -0.0608   0.9771   0.0107
  -5.250  -0.0024   0.01471   0.01119  -0.1381   0.9629   0.0113
  -5.000   0.0321   0.01327   0.00949  -0.1400   0.9599   0.0111
  -4.750   0.0635   0.01265   0.00875  -0.1408   0.9557   0.0108
  -4.500   0.0964   0.01072   0.00651  -0.1423   0.9518   0.0106
  -4.250   0.1308   0.00964   0.00522  -0.1438   0.9482   0.0107
  -4.000   0.1551   0.00804   0.00336  -0.1431   0.9421   0.0120
  -3.750   0.1847   0.00770   0.00296  -0.1434   0.9372   0.0134
  -3.500   0.2132   0.00744   0.00263  -0.1434   0.9321   0.0149
  -3.250   0.2399   0.00721   0.00232  -0.1430   0.9260   0.0161
  -3.000   0.2689   0.00681   0.00183  -0.1430   0.9207   0.0214
  -2.750   0.2942   0.00662   0.00162  -0.1423   0.9135   0.0273
  -2.500   0.3223   0.00636   0.00137  -0.1422   0.9074   0.0444
  -2.250   0.3474   0.00605   0.00121  -0.1415   0.8995   0.0906
  -2.000   0.3745   0.00583   0.00109  -0.1413   0.8920   0.1401
  -1.750   0.4006   0.00568   0.00102  -0.1408   0.8820   0.1747
  -1.500   0.4270   0.00560   0.00095  -0.1403   0.8708   0.1972
  -1.250   0.4535   0.00555   0.00089  -0.1398   0.8576   0.2156
  -1.000   0.4797   0.00551   0.00084  -0.1392   0.8414   0.2379
  -0.750   0.5055   0.00550   0.00081  -0.1386   0.8221   0.2601
  -0.500   0.5307   0.00554   0.00078  -0.1378   0.7985   0.2766
  -0.250   0.5555   0.00561   0.00078  -0.1369   0.7723   0.2916
   0.000   0.5800   0.00571   0.00079  -0.1360   0.7453   0.3070
   0.250   0.6046   0.00581   0.00082  -0.1352   0.7199   0.3222
   0.500   0.6292   0.00593   0.00086  -0.1344   0.6957   0.3388
   0.750   0.6541   0.00603   0.00091  -0.1336   0.6736   0.3559
   1.000   0.6793   0.00612   0.00097  -0.1329   0.6535   0.3748
   1.500   0.7299   0.00629   0.00111  -0.1317   0.6164   0.4197
   1.750   0.7553   0.00636   0.00119  -0.1311   0.5994   0.4503
   2.000   0.7807   0.00640   0.00129  -0.1305   0.5824   0.4924
   2.250   0.8054   0.00633   0.00142  -0.1298   0.5659   0.5929
   2.500   0.8372   0.00575   0.00156  -0.1308   0.5482   1.0000
   2.750   0.8628   0.00592   0.00165  -0.1303   0.5315   1.0000
   3.000   0.8885   0.00607   0.00176  -0.1297   0.5144   1.0000
   3.250   0.9141   0.00624   0.00187  -0.1292   0.4967   1.0000
   3.500   0.9394   0.00642   0.00200  -0.1286   0.4781   1.0000
   3.750   0.9634   0.00671   0.00214  -0.1278   0.4445   1.0000
   4.000   0.9854   0.00719   0.00234  -0.1267   0.3871   1.0000
   4.250   1.0076   0.00767   0.00259  -0.1256   0.3353   1.0000
   4.500   1.0314   0.00803   0.00281  -0.1248   0.3014   1.0000
   4.750   1.0546   0.00846   0.00307  -0.1239   0.2648   1.0000
   5.000   1.0770   0.00897   0.00337  -0.1230   0.2207   1.0000
   5.250   1.0979   0.00964   0.00377  -0.1218   0.1656   1.0000
   5.500   1.1145   0.01080   0.00444  -0.1199   0.0762   1.0000
   5.750   1.1337   0.01172   0.00509  -0.1184   0.0277   1.0000
   6.000   1.1565   0.01222   0.00557  -0.1174   0.0187   1.0000
   6.250   1.1782   0.01288   0.00629  -0.1161   0.0142   1.0000
   6.500   1.2012   0.01333   0.00680  -0.1151   0.0133   1.0000
   6.750   1.2249   0.01368   0.00718  -0.1144   0.0124   1.0000
   7.000   1.2476   0.01413   0.00768  -0.1134   0.0114   1.0000
   7.250   1.2698   0.01462   0.00820  -0.1124   0.0104   1.0000
   7.500   1.2862   0.01577   0.00949  -0.1103   0.0089   1.0000
   7.750   1.3058   0.01650   0.01030  -0.1088   0.0083   1.0000
   8.000   1.3275   0.01697   0.01081  -0.1078   0.0078   1.0000
   8.250   1.3484   0.01750   0.01139  -0.1066   0.0071   1.0000
   8.500   1.3696   0.01797   0.01187  -0.1056   0.0064   1.0000
   8.750   1.3880   0.01871   0.01267  -0.1040   0.0058   1.0000
   9.000   1.3913   0.02104   0.01521  -0.0999   0.0052   1.0000
   9.250   1.4056   0.02220   0.01649  -0.0978   0.0051   1.0000
   9.500   1.4222   0.02302   0.01739  -0.0960   0.0049   1.0000
   9.750   1.4365   0.02407   0.01856  -0.0939   0.0048   1.0000
  10.000   1.4495   0.02516   0.01976  -0.0916   0.0046   1.0000
  10.250   1.4591   0.02638   0.02110  -0.0887   0.0045   1.0000
  10.500   1.4679   0.02757   0.02240  -0.0858   0.0043   1.0000
  10.750   1.4746   0.02900   0.02396  -0.0828   0.0041   1.0000
  11.000   1.4813   0.03027   0.02535  -0.0799   0.0039   1.0000
  11.250   1.4852   0.03191   0.02714  -0.0768   0.0038   1.0000
  11.500   1.4902   0.03321   0.02858  -0.0741   0.0036   1.0000
  11.750   1.4933   0.03478   0.03026  -0.0715   0.0035   1.0000
  12.000   1.4928   0.03690   0.03254  -0.0687   0.0034   1.0000
  12.250   1.4945   0.03860   0.03435  -0.0665   0.0033   1.0000
  12.500   1.4941   0.04064   0.03651  -0.0644   0.0032   1.0000
  12.750   1.4880   0.04359   0.03963  -0.0623   0.0032   1.0000
  13.000   1.4801   0.04688   0.04309  -0.0607   0.0031   1.0000
  13.250   1.4690   0.05077   0.04717  -0.0596   0.0031   1.0000
  13.500   1.4550   0.05539   0.05199  -0.0591   0.0031   1.0000
  13.750   1.4382   0.06072   0.05753  -0.0596   0.0030   1.0000
  14.000   1.4218   0.06643   0.06344  -0.0608   0.0030   1.0000
  14.250   1.4042   0.07279   0.06999  -0.0629   0.0030   1.0000
  14.500   1.3858   0.07979   0.07717  -0.0658   0.0030   1.0000
  14.750   1.3666   0.08749   0.08506  -0.0695   0.0031   1.0000
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