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Glenn Martin 2 (glennmartin2-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: Glenn Martin 2 (glennmartin2-il)
Reynolds number: 500,000
Max Cl/Cd: 78.56 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-glennmartin2-il-500000-n5.txt
Download as CSV file: xf-glennmartin2-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Glenn Martin 2                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.1524   0.10987   0.10750  -0.0722   0.9690   0.0098
 -12.000  -0.5111   0.03197   0.02868  -0.1236   0.9355   0.0111
 -11.750  -0.5075   0.02653   0.02282  -0.1243   0.9276   0.0112
 -11.500  -0.4873   0.02411   0.02007  -0.1251   0.9230   0.0116
 -11.250  -0.4640   0.02224   0.01799  -0.1257   0.9189   0.0120
 -11.000  -0.4463   0.02111   0.01672  -0.1245   0.9118   0.0125
 -10.750  -0.4187   0.02003   0.01547  -0.1251   0.9058   0.0130
 -10.500  -0.3973   0.01913   0.01441  -0.1243   0.8975   0.0135
 -10.250  -0.3721   0.01827   0.01337  -0.1241   0.8901   0.0141
 -10.000  -0.3512   0.01755   0.01247  -0.1229   0.8833   0.0148
  -9.750  -0.3282   0.01687   0.01166  -0.1220   0.8751   0.0155
  -9.500  -0.3050   0.01641   0.01113  -0.1211   0.8675   0.0163
  -9.250  -0.2807   0.01602   0.01065  -0.1204   0.8595   0.0174
  -9.000  -0.2580   0.01558   0.01007  -0.1192   0.8511   0.0184
  -8.750  -0.2347   0.01511   0.00946  -0.1183   0.8425   0.0192
  -8.500  -0.2124   0.01474   0.00904  -0.1171   0.8339   0.0202
  -8.250  -0.1879   0.01445   0.00865  -0.1162   0.8246   0.0213
  -8.000  -0.1654   0.01414   0.00823  -0.1150   0.8129   0.0224
  -7.750  -0.1420   0.01390   0.00785  -0.1139   0.8000   0.0236
  -7.500  -0.1205   0.01353   0.00737  -0.1124   0.7840   0.0247
  -7.250  -0.0990   0.01333   0.00705  -0.1109   0.7626   0.0260
  -7.000  -0.0785   0.01315   0.00672  -0.1092   0.7353   0.0271
  -6.750  -0.0598   0.01304   0.00641  -0.1071   0.7042   0.0283
  -6.500  -0.0413   0.01297   0.00614  -0.1049   0.6781   0.0294
  -6.250  -0.0224   0.01281   0.00581  -0.1028   0.6586   0.0303
  -6.000  -0.0023   0.01259   0.00549  -0.1011   0.6453   0.0318
  -5.750   0.0194   0.01245   0.00526  -0.0997   0.6349   0.0332
  -5.500   0.0418   0.01231   0.00504  -0.0984   0.6255   0.0346
  -5.250   0.0642   0.01219   0.00482  -0.0971   0.6161   0.0360
  -5.000   0.0864   0.01208   0.00460  -0.0958   0.6065   0.0370
  -4.750   0.1089   0.01186   0.00433  -0.0945   0.5977   0.0387
  -4.500   0.1311   0.01174   0.00416  -0.0932   0.5889   0.0406
  -4.250   0.1541   0.01161   0.00398  -0.0920   0.5786   0.0427
  -4.000   0.1763   0.01152   0.00382  -0.0907   0.5675   0.0446
  -3.750   0.1978   0.01142   0.00367  -0.0892   0.5530   0.0475
  -3.500   0.2178   0.01138   0.00356  -0.0875   0.5298   0.0514
  -3.250   0.2326   0.01149   0.00348  -0.0846   0.4839   0.0556
  -3.000   0.2435   0.01176   0.00351  -0.0811   0.4317   0.0606
  -2.750   0.2612   0.01192   0.00353  -0.0789   0.4074   0.0655
  -2.500   0.2803   0.01198   0.00350  -0.0771   0.3927   0.0696
  -2.250   0.2995   0.01202   0.00348  -0.0752   0.3818   0.0738
  -2.000   0.3195   0.01206   0.00346  -0.0735   0.3725   0.0776
  -1.750   0.3394   0.01212   0.00343  -0.0718   0.3651   0.0800
  -1.500   0.3597   0.01211   0.00339  -0.0701   0.3591   0.0833
  -1.250   0.3795   0.01211   0.00336  -0.0684   0.3533   0.0877
  -1.000   0.3998   0.01213   0.00335  -0.0668   0.3490   0.0917
  -0.750   0.4209   0.01215   0.00335  -0.0654   0.3449   0.0959
  -0.500   0.4411   0.01216   0.00335  -0.0638   0.3409   0.1030
  -0.250   0.4613   0.01219   0.00337  -0.0622   0.3372   0.1103
   0.000   0.4807   0.01221   0.00341  -0.0605   0.3340   0.1267
   0.250   0.5002   0.01215   0.00352  -0.0589   0.3314   0.1844
   0.500   0.5214   0.01220   0.00362  -0.0576   0.3290   0.2093
   0.750   0.5426   0.01228   0.00372  -0.0562   0.3263   0.2258
   1.000   0.5638   0.01238   0.00381  -0.0549   0.3236   0.2375
   1.250   0.5845   0.01249   0.00391  -0.0536   0.3213   0.2457
   1.500   0.6048   0.01263   0.00402  -0.0521   0.3185   0.2521
   1.750   0.6254   0.01275   0.00413  -0.0508   0.3165   0.2593
   2.000   0.6473   0.01283   0.00423  -0.0497   0.3146   0.2663
   2.250   0.6687   0.01293   0.00434  -0.0485   0.3127   0.2720
   2.500   0.6899   0.01303   0.00446  -0.0473   0.3110   0.2781
   2.750   0.7110   0.01316   0.00458  -0.0461   0.3092   0.2853
   3.000   0.7313   0.01327   0.00472  -0.0448   0.3074   0.2965
   3.250   0.7516   0.01339   0.00487  -0.0435   0.3057   0.3055
   3.500   0.7717   0.01352   0.00502  -0.0422   0.3042   0.3188
   3.750   0.7911   0.01364   0.00520  -0.0408   0.3026   0.3427
   4.000   0.7897   0.01276   0.00543  -0.0351   0.3012   0.7870
   4.500   1.0598   0.01365   0.00668  -0.0835   0.2929   1.0000
   4.750   1.0768   0.01383   0.00685  -0.0815   0.2912   1.0000
   5.000   1.0934   0.01403   0.00704  -0.0796   0.2892   1.0000
   5.250   1.1099   0.01425   0.00725  -0.0777   0.2873   1.0000
   5.500   1.1260   0.01451   0.00749  -0.0758   0.2852   1.0000
   5.750   1.1446   0.01468   0.00769  -0.0743   0.2836   1.0000
   6.000   1.1632   0.01485   0.00790  -0.0728   0.2817   1.0000
   6.250   1.1816   0.01504   0.00811  -0.0714   0.2789   1.0000
   6.500   1.1989   0.01526   0.00833  -0.0698   0.2750   1.0000
   6.750   1.2148   0.01554   0.00859  -0.0680   0.2712   1.0000
   7.000   1.2331   0.01575   0.00882  -0.0666   0.2662   1.0000
   7.250   1.2511   0.01599   0.00908  -0.0652   0.2617   1.0000
   7.500   1.2667   0.01632   0.00938  -0.0635   0.2560   1.0000
   7.750   1.2847   0.01659   0.00968  -0.0622   0.2504   1.0000
   8.000   1.3007   0.01694   0.01001  -0.0606   0.2427   1.0000
   8.250   1.3161   0.01734   0.01039  -0.0590   0.2313   1.0000
   8.500   1.3275   0.01794   0.01090  -0.0569   0.2123   1.0000
   8.750   1.3280   0.01917   0.01186  -0.0533   0.1750   1.0000
   9.000   1.3290   0.02046   0.01299  -0.0500   0.1501   1.0000
   9.250   1.3260   0.02205   0.01439  -0.0463   0.1209   1.0000
   9.500   1.3048   0.02483   0.01682  -0.0407   0.0664   1.0000
   9.750   1.2881   0.02753   0.01938  -0.0361   0.0212   1.0000
  10.000   1.2935   0.02885   0.02075  -0.0342   0.0160   1.0000
  10.250   1.3008   0.03009   0.02205  -0.0325   0.0143   1.0000
  10.500   1.3088   0.03131   0.02335  -0.0311   0.0133   1.0000
  10.750   1.3165   0.03260   0.02471  -0.0298   0.0125   1.0000
  11.000   1.3225   0.03409   0.02628  -0.0284   0.0118   1.0000
  11.250   1.3272   0.03575   0.02802  -0.0271   0.0112   1.0000
  11.500   1.3290   0.03775   0.03013  -0.0258   0.0106   1.0000
  11.750   1.3330   0.03963   0.03210  -0.0248   0.0102   1.0000
  12.000   1.3362   0.04167   0.03423  -0.0240   0.0099   1.0000
  12.250   1.3383   0.04391   0.03656  -0.0233   0.0096   1.0000
  12.500   1.3397   0.04630   0.03904  -0.0227   0.0090   1.0000
  12.750   1.3380   0.04911   0.04196  -0.0222   0.0088   1.0000
  13.000   1.3361   0.05200   0.04495  -0.0218   0.0084   1.0000
  13.250   1.3305   0.05541   0.04846  -0.0215   0.0083   1.0000
  13.500   1.3216   0.05933   0.05250  -0.0214   0.0081   1.0000
  13.750   1.3139   0.06319   0.05647  -0.0215   0.0080   1.0000
  14.000   1.3008   0.06793   0.06135  -0.0218   0.0078   1.0000
  14.250   1.2930   0.07213   0.06568  -0.0223   0.0077   1.0000
  14.500   1.2815   0.07699   0.07066  -0.0230   0.0077   1.0000
  14.750   1.2697   0.08199   0.07578  -0.0239   0.0076   1.0000
  15.000   1.2587   0.08694   0.08085  -0.0249   0.0075   1.0000
  15.250   1.2475   0.09195   0.08597  -0.0259   0.0072   1.0000
  15.500   1.2339   0.09732   0.09146  -0.0270   0.0073   1.0000
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