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GM15 (smoothed) (gm15sm-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GM15 (smoothed) (gm15sm-il)
Reynolds number: 100,000
Max Cl/Cd: 66.21 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-gm15sm-il-100000.txt
Download as CSV file: xf-gm15sm-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3467   0.10526   0.10043  -0.0289   1.0000   0.0743
  -7.750  -0.3611   0.10520   0.10051  -0.0287   1.0000   0.0747
  -7.500  -0.3715   0.10458   0.10001  -0.0299   1.0000   0.0750
  -7.250  -0.3431   0.09623   0.09159  -0.0254   1.0000   0.0780
  -7.000  -0.3428   0.09405   0.08947  -0.0235   1.0000   0.0802
  -6.750  -0.3481   0.09238   0.08788  -0.0215   1.0000   0.0822
  -6.500  -0.3529   0.09061   0.08618  -0.0209   1.0000   0.0850
  -6.250  -0.3593   0.08967   0.08534  -0.0251   1.0000   0.0878
  -6.000  -0.3562   0.08693   0.08267  -0.0317   1.0000   0.0890
  -5.750  -0.3548   0.08322   0.07900  -0.0240   1.0000   0.0907
  -5.500  -0.3504   0.08067   0.07648  -0.0218   1.0000   0.0934
  -5.250  -0.3445   0.07817   0.07401  -0.0227   1.0000   0.0974
  -5.000  -0.3251   0.07419   0.07003  -0.0347   1.0000   0.1031
  -4.750  -0.3236   0.07161   0.06750  -0.0296   1.0000   0.1051
  -4.500  -0.3143   0.06907   0.06494  -0.0292   1.0000   0.1098
  -4.250  -0.2869   0.06463   0.06044  -0.0386   1.0000   0.1178
  -4.000  -0.2789   0.06230   0.05815  -0.0364   1.0000   0.1215
  -3.500  -0.2190   0.05463   0.05029  -0.0498   1.0000   0.1451
  -3.250  -0.1964   0.05183   0.04745  -0.0521   1.0000   0.1592
  -3.000  -0.0584   0.02949   0.02317  -0.0855   1.0000   0.0710
  -2.750  -0.0158   0.02494   0.01764  -0.0892   1.0000   0.0660
  -2.500   0.0149   0.02282   0.01497  -0.0900   1.0000   0.0669
  -2.250   0.0414   0.02163   0.01342  -0.0899   1.0000   0.0719
  -2.000   0.0664   0.02061   0.01222  -0.0897   1.0000   0.0813
  -1.750   0.0915   0.01968   0.01113  -0.0893   1.0000   0.0914
  -1.500   0.1148   0.01921   0.01068  -0.0889   1.0000   0.1167
  -1.250   0.1586   0.01875   0.01065  -0.0923   0.9938   0.2289
  -1.000   0.2032   0.01933   0.01131  -0.0959   0.9843   0.3083
  -0.750   0.2476   0.01958   0.01157  -0.0995   0.9751   0.3586
  -0.500   0.2895   0.01956   0.01152  -0.1024   0.9647   0.3972
  -0.250   0.3315   0.01945   0.01145  -0.1054   0.9545   0.4330
   0.000   0.3776   0.01927   0.01129  -0.1090   0.9454   0.4723
   0.250   0.4245   0.01897   0.01106  -0.1127   0.9362   0.5180
   0.500   0.4669   0.01855   0.01085  -0.1154   0.9252   0.5778
   0.750   0.5124   0.01734   0.01045  -0.1185   0.9159   1.0000
   1.000   0.5645   0.01719   0.01005  -0.1229   0.9077   1.0000
   1.250   0.6059   0.01707   0.00981  -0.1252   0.8953   1.0000
   1.500   0.6473   0.01690   0.00958  -0.1274   0.8831   1.0000
   1.750   0.6869   0.01667   0.00932  -0.1290   0.8705   1.0000
   2.000   0.7253   0.01639   0.00903  -0.1302   0.8575   1.0000
   2.250   0.7623   0.01609   0.00877  -0.1311   0.8439   1.0000
   2.500   0.7979   0.01579   0.00849  -0.1317   0.8294   1.0000
   2.750   0.8326   0.01551   0.00822  -0.1320   0.8139   1.0000
   3.000   0.8667   0.01525   0.00797  -0.1322   0.7977   1.0000
   3.250   0.8955   0.01519   0.00798  -0.1316   0.7777   1.0000
   3.500   0.9261   0.01512   0.00791  -0.1312   0.7580   1.0000
   3.750   0.9544   0.01519   0.00799  -0.1305   0.7366   1.0000
   4.000   0.9828   0.01531   0.00809  -0.1299   0.7150   1.0000
   4.250   1.0085   0.01556   0.00836  -0.1288   0.6915   1.0000
   4.500   1.0349   0.01585   0.00871  -0.1279   0.6686   1.0000
   4.750   1.0603   0.01619   0.00905  -0.1268   0.6450   1.0000
   5.000   1.0841   0.01658   0.00950  -0.1255   0.6201   1.0000
   5.250   1.1077   0.01698   0.00994  -0.1241   0.5946   1.0000
   5.500   1.1274   0.01715   0.01002  -0.1216   0.5570   1.0000
   5.750   1.1422   0.01725   0.01004  -0.1182   0.5054   1.0000
   6.000   1.1587   0.01759   0.01031  -0.1156   0.4575   1.0000
   6.250   1.1739   0.01809   0.01070  -0.1128   0.3997   1.0000
   6.500   1.1784   0.01952   0.01138  -0.1085   0.2592   1.0000
   6.750   1.1720   0.02346   0.01373  -0.1034   0.0919   1.0000
   7.000   1.1828   0.02542   0.01563  -0.1005   0.0715   1.0000
   7.250   1.1934   0.02736   0.01759  -0.0976   0.0633   1.0000
   7.500   1.2079   0.02920   0.01945  -0.0952   0.0580   1.0000
   7.750   1.2285   0.03226   0.02238  -0.0939   0.0540   1.0000
   8.000   1.2530   0.03415   0.02452  -0.0928   0.0505   1.0000
   8.250   1.2764   0.03638   0.02689  -0.0918   0.0462   1.0000
   8.500   1.3040   0.03965   0.03033  -0.0913   0.0446   1.0000
   8.750   1.3282   0.04329   0.03429  -0.0903   0.0442   1.0000
   9.000   1.3469   0.04695   0.03842  -0.0884   0.0447   1.0000
   9.250   1.3603   0.05100   0.04283  -0.0865   0.0438   1.0000
   9.500   1.3685   0.05601   0.04820  -0.0845   0.0430   1.0000
   9.750   1.3737   0.05995   0.05258  -0.0819   0.0431   1.0000
  10.000   1.3605   0.06283   0.05637  -0.0762   0.0461   1.0000
  10.250   1.3464   0.06801   0.06210  -0.0723   0.0491   1.0000
  10.500   1.3357   0.07304   0.06741  -0.0695   0.0512   1.0000
  10.750   1.2190   0.07066   0.06561  -0.0570   0.0491   1.0000
  11.000   1.1925   0.07578   0.07096  -0.0553   0.0498   1.0000
  11.250   1.1652   0.08143   0.07681  -0.0549   0.0506   1.0000
  11.500   1.1377   0.08757   0.08314  -0.0556   0.0513   1.0000
  11.750   1.1116   0.09415   0.08987  -0.0573   0.0523   1.0000
  12.000   1.0855   0.10103   0.09688  -0.0598   0.0530   1.0000
  12.250   1.0030   0.11480   0.11106  -0.0716   0.0587   1.0000
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