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GM15 (smoothed) (gm15sm-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GM15 (smoothed) (gm15sm-il)
Reynolds number: 500,000
Max Cl/Cd: 112.35 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-gm15sm-il-500000-n5.txt
Download as CSV file: xf-gm15sm-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3456   0.09591   0.09367  -0.0261   1.0000   0.0096
  -8.000  -0.3492   0.09374   0.09154  -0.0248   1.0000   0.0090
  -7.750  -0.3357   0.08923   0.08703  -0.0293   0.9980   0.0084
  -7.500  -0.3219   0.08438   0.08220  -0.0343   0.9928   0.0080
  -7.250  -0.3100   0.07992   0.07774  -0.0389   0.9830   0.0079
  -7.000  -0.2914   0.07471   0.07253  -0.0455   0.9759   0.0078
  -6.750  -0.2712   0.06963   0.06744  -0.0526   0.9708   0.0079
  -6.500  -0.2456   0.06432   0.06211  -0.0610   0.9667   0.0082
  -6.250  -0.2123   0.05767   0.05543  -0.0726   0.9636   0.0084
  -5.750  -0.0869   0.01969   0.01597  -0.1294   0.9545   0.0086
  -5.500  -0.0502   0.01599   0.01161  -0.1332   0.9517   0.0086
  -5.250  -0.0146   0.01395   0.00916  -0.1356   0.9493   0.0087
  -5.000   0.0161   0.01265   0.00757  -0.1366   0.9452   0.0091
  -4.750   0.0459   0.01167   0.00638  -0.1371   0.9405   0.0094
  -4.500   0.0782   0.01091   0.00542  -0.1382   0.9367   0.0101
  -4.250   0.1079   0.01039   0.00477  -0.1385   0.9320   0.0106
  -4.000   0.1355   0.00968   0.00394  -0.1385   0.9262   0.0117
  -3.750   0.1663   0.00929   0.00346  -0.1391   0.9215   0.0129
  -3.500   0.1925   0.00905   0.00318  -0.1387   0.9148   0.0149
  -3.250   0.2214   0.00881   0.00285  -0.1387   0.9087   0.0168
  -3.000   0.2483   0.00843   0.00242  -0.1384   0.9015   0.0215
  -2.750   0.2767   0.00823   0.00214  -0.1383   0.8942   0.0261
  -2.500   0.3033   0.00800   0.00192  -0.1379   0.8852   0.0382
  -2.250   0.3307   0.00772   0.00171  -0.1377   0.8757   0.0672
  -2.000   0.3579   0.00746   0.00154  -0.1375   0.8645   0.1111
  -1.750   0.3850   0.00732   0.00142  -0.1372   0.8511   0.1419
  -1.500   0.4119   0.00721   0.00133  -0.1369   0.8352   0.1722
  -1.250   0.4387   0.00713   0.00127  -0.1365   0.8168   0.2033
  -1.000   0.4651   0.00712   0.00120  -0.1360   0.7952   0.2283
  -0.750   0.4908   0.00716   0.00115  -0.1353   0.7699   0.2451
  -0.500   0.5160   0.00723   0.00113  -0.1345   0.7436   0.2601
  -0.250   0.5410   0.00733   0.00113  -0.1338   0.7188   0.2747
   0.000   0.5660   0.00743   0.00115  -0.1330   0.6956   0.2892
   0.250   0.5910   0.00753   0.00118  -0.1323   0.6736   0.3042
   0.500   0.6162   0.00763   0.00122  -0.1316   0.6538   0.3192
   0.750   0.6415   0.00773   0.00128  -0.1309   0.6347   0.3349
   1.000   0.6667   0.00784   0.00135  -0.1303   0.6166   0.3508
   1.500   0.7176   0.00803   0.00150  -0.1291   0.5818   0.3867
   1.750   0.7430   0.00812   0.00159  -0.1285   0.5650   0.4082
   2.000   0.7683   0.00822   0.00171  -0.1279   0.5481   0.4331
   2.250   0.7935   0.00831   0.00183  -0.1273   0.5321   0.4648
   2.500   0.8186   0.00836   0.00196  -0.1267   0.5159   0.5124
   2.750   0.8406   0.00806   0.00215  -0.1255   0.5001   0.7196
   3.250   0.9002   0.00803   0.00242  -0.1263   0.4647   1.0000
   3.500   0.9253   0.00825   0.00258  -0.1257   0.4471   1.0000
   3.750   0.9505   0.00846   0.00274  -0.1251   0.4291   1.0000
   4.000   0.9754   0.00870   0.00293  -0.1244   0.4096   1.0000
   4.250   0.9978   0.00915   0.00320  -0.1234   0.3659   1.0000
   4.500   1.0184   0.00981   0.00352  -0.1221   0.3009   1.0000
   4.750   1.0391   0.01051   0.00389  -0.1209   0.2395   1.0000
   5.000   1.0598   0.01123   0.00431  -0.1198   0.1816   1.0000
   5.250   1.0793   0.01211   0.00484  -0.1185   0.1158   1.0000
   5.500   1.0982   0.01307   0.00548  -0.1170   0.0564   1.0000
   5.750   1.1196   0.01374   0.00604  -0.1159   0.0309   1.0000
   6.000   1.1422   0.01426   0.00653  -0.1150   0.0214   1.0000
   6.250   1.1654   0.01469   0.00701  -0.1141   0.0179   1.0000
   6.500   1.1873   0.01528   0.00763  -0.1130   0.0145   1.0000
   6.750   1.2096   0.01578   0.00819  -0.1120   0.0129   1.0000
   7.000   1.2316   0.01631   0.00880  -0.1109   0.0118   1.0000
   7.250   1.2530   0.01688   0.00946  -0.1098   0.0108   1.0000
   7.500   1.2738   0.01750   0.01011  -0.1086   0.0097   1.0000
   7.750   1.2917   0.01840   0.01110  -0.1069   0.0085   1.0000
   8.000   1.3118   0.01903   0.01181  -0.1056   0.0080   1.0000
   8.250   1.3308   0.01975   0.01262  -0.1042   0.0075   1.0000
   8.500   1.3487   0.02054   0.01351  -0.1025   0.0069   1.0000
   8.750   1.3662   0.02133   0.01438  -0.1009   0.0064   1.0000
   9.000   1.3827   0.02218   0.01533  -0.0992   0.0060   1.0000
   9.250   1.3959   0.02329   0.01653  -0.0969   0.0055   1.0000
   9.500   1.4027   0.02499   0.01836  -0.0937   0.0051   1.0000
   9.750   1.4157   0.02586   0.01935  -0.0914   0.0050   1.0000
  10.000   1.4278   0.02674   0.02034  -0.0890   0.0047   1.0000
  10.250   1.4374   0.02780   0.02153  -0.0863   0.0044   1.0000
  10.500   1.4462   0.02892   0.02278  -0.0836   0.0041   1.0000
  10.750   1.4521   0.03035   0.02435  -0.0807   0.0040   1.0000
  11.000   1.4577   0.03182   0.02596  -0.0780   0.0038   1.0000
  11.250   1.4619   0.03345   0.02775  -0.0753   0.0037   1.0000
  11.500   1.4661   0.03510   0.02954  -0.0728   0.0035   1.0000
  11.750   1.4689   0.03692   0.03154  -0.0705   0.0034   1.0000
  12.000   1.4701   0.03900   0.03378  -0.0682   0.0034   1.0000
  12.250   1.4715   0.04103   0.03595  -0.0663   0.0033   1.0000
  12.500   1.4718   0.04326   0.03832  -0.0646   0.0032   1.0000
  12.750   1.4692   0.04599   0.04122  -0.0632   0.0031   1.0000
  13.000   1.4652   0.04901   0.04440  -0.0621   0.0031   1.0000
  13.250   1.4589   0.05250   0.04807  -0.0614   0.0030   1.0000
  13.500   1.4497   0.05662   0.05239  -0.0612   0.0030   1.0000
  13.750   1.4378   0.06141   0.05737  -0.0617   0.0029   1.0000
  14.000   1.4239   0.06686   0.06303  -0.0628   0.0029   1.0000
  14.250   1.4072   0.07310   0.06950  -0.0648   0.0028   1.0000
  14.500   1.3896   0.07997   0.07658  -0.0675   0.0028   1.0000
  14.750   1.3726   0.08718   0.08399  -0.0708   0.0028   1.0000
  15.000   1.3562   0.09473   0.09171  -0.0746   0.0028   1.0000
  15.250   1.3380   0.10314   0.10031  -0.0792   0.0028   1.0000
  15.500   1.3207   0.11179   0.10912  -0.0841   0.0028   1.0000
  15.750   1.3047   0.12058   0.11808  -0.0893   0.0028   1.0000
  16.000   1.2890   0.12979   0.12743  -0.0948   0.0029   1.0000
  16.250   1.2705   0.14015   0.13795  -0.1011   0.0029   1.0000
  16.500   1.2480   0.15241   0.15036  -0.1086   0.0030   1.0000
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