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Glenn Martin 2 (glennmartin2-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: Glenn Martin 2 (glennmartin2-il)
Reynolds number: 500,000
Max Cl/Cd: 78.39 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-glennmartin2-il-500000.txt
Download as CSV file: xf-glennmartin2-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.1113   0.09728   0.09506  -0.0761   0.9741   0.0267
 -10.500  -0.0951   0.09395   0.09173  -0.0795   0.9723   0.0281
  -9.750  -0.3091   0.02904   0.02574  -0.1204   0.9359   0.0220
  -9.500  -0.2826   0.02727   0.02380  -0.1217   0.9325   0.0227
  -9.250  -0.2585   0.02467   0.02084  -0.1229   0.9292   0.0237
  -9.000  -0.2503   0.02280   0.01862  -0.1200   0.9204   0.0245
  -8.750  -0.2245   0.02137   0.01681  -0.1201   0.9158   0.0253
  -8.500  -0.2096   0.01951   0.01477  -0.1184   0.9087   0.0265
  -8.250  -0.1838   0.01907   0.01429  -0.1180   0.9027   0.0275
  -8.000  -0.1520   0.01825   0.01330  -0.1190   0.8981   0.0289
  -7.750  -0.1369   0.01755   0.01241  -0.1163   0.8893   0.0299
  -7.500  -0.1098   0.01641   0.01098  -0.1161   0.8831   0.0310
  -7.250  -0.0928   0.01561   0.01013  -0.1140   0.8744   0.0324
  -7.000  -0.0630   0.01526   0.00970  -0.1142   0.8670   0.0340
  -6.750  -0.0439   0.01482   0.00916  -0.1122   0.8567   0.0354
  -6.500  -0.0181   0.01434   0.00852  -0.1115   0.8481   0.0366
  -6.250   0.0036   0.01344   0.00748  -0.1102   0.8377   0.0382
  -6.000   0.0259   0.01309   0.00710  -0.1088   0.8262   0.0398
  -5.750   0.0498   0.01280   0.00673  -0.1077   0.8140   0.0415
  -5.500   0.0732   0.01248   0.00629  -0.1065   0.8000   0.0431
  -5.250   0.0961   0.01224   0.00593  -0.1052   0.7840   0.0445
  -5.000   0.1166   0.01171   0.00532  -0.1035   0.7640   0.0468
  -4.750   0.1375   0.01158   0.00507  -0.1017   0.7394   0.0490
  -4.500   0.1571   0.01147   0.00480  -0.0997   0.7123   0.0510
  -4.250   0.1768   0.01146   0.00461  -0.0977   0.6885   0.0530
  -4.000   0.1958   0.01121   0.00428  -0.0957   0.6704   0.0565
  -3.750   0.2172   0.01121   0.00419  -0.0941   0.6561   0.0603
  -3.500   0.2389   0.01118   0.00404  -0.0927   0.6436   0.0640
  -3.250   0.2599   0.01108   0.00391  -0.0911   0.6317   0.0706
  -3.000   0.2822   0.01106   0.00381  -0.0898   0.6201   0.0769
  -2.750   0.3031   0.01094   0.00367  -0.0882   0.6084   0.0844
  -2.500   0.3244   0.01098   0.00362  -0.0867   0.5956   0.0893
  -2.250   0.3430   0.01083   0.00343  -0.0846   0.5807   0.0957
  -2.000   0.3616   0.01079   0.00334  -0.0826   0.5605   0.1011
  -1.750   0.3763   0.01085   0.00325  -0.0796   0.5245   0.1047
  -1.500   0.3783   0.01111   0.00319  -0.0742   0.4572   0.1091
  -1.250   0.3869   0.01133   0.00322  -0.0702   0.4245   0.1141
  -1.000   0.4018   0.01147   0.00324  -0.0675   0.4074   0.1200
  -0.750   0.4184   0.01150   0.00326  -0.0651   0.3960   0.1335
  -0.500   0.4349   0.01145   0.00339  -0.0628   0.3878   0.1900
  -0.250   0.4543   0.01157   0.00353  -0.0610   0.3808   0.2318
   0.000   0.4737   0.01174   0.00365  -0.0593   0.3751   0.2483
   0.250   0.4953   0.01185   0.00374  -0.0580   0.3699   0.2610
   0.500   0.5155   0.01196   0.00385  -0.0564   0.3654   0.2710
   0.750   0.5354   0.01214   0.00396  -0.0549   0.3612   0.2801
   1.000   0.5563   0.01224   0.00406  -0.0535   0.3578   0.2881
   1.250   0.5778   0.01232   0.00414  -0.0522   0.3547   0.2960
   1.500   0.5985   0.01241   0.00423  -0.0508   0.3516   0.3037
   1.750   0.6190   0.01253   0.00433  -0.0494   0.3488   0.3112
   2.000   0.6390   0.01267   0.00446  -0.0480   0.3458   0.3202
   2.250   0.6595   0.01280   0.00460  -0.0466   0.3429   0.3331
   2.500   0.6796   0.01279   0.00472  -0.0452   0.3408   0.3624
   2.750   0.9618   0.01287   0.00613  -0.1017   0.3322   1.0000
   3.000   0.9788   0.01307   0.00629  -0.0997   0.3302   1.0000
   3.250   0.9972   0.01337   0.00653  -0.0981   0.3276   1.0000
   3.500   1.0135   0.01348   0.00665  -0.0959   0.3264   1.0000
   3.750   1.0283   0.01358   0.00676  -0.0934   0.3246   1.0000
   4.000   1.0433   0.01369   0.00688  -0.0909   0.3225   1.0000
   4.250   1.0593   0.01383   0.00702  -0.0887   0.3204   1.0000
   4.500   1.0746   0.01396   0.00715  -0.0864   0.3179   1.0000
   4.750   1.0913   0.01415   0.00731  -0.0844   0.3158   1.0000
   5.000   1.1099   0.01440   0.00754  -0.0828   0.3138   1.0000
   5.250   1.1319   0.01475   0.00784  -0.0820   0.3114   1.0000
   5.500   1.1478   0.01486   0.00800  -0.0799   0.3100   1.0000
   5.750   1.1643   0.01500   0.00818  -0.0779   0.3082   1.0000
   6.000   1.1785   0.01510   0.00832  -0.0755   0.3049   1.0000
   6.250   1.1937   0.01525   0.00847  -0.0733   0.3017   1.0000
   6.500   1.2104   0.01548   0.00869  -0.0715   0.2990   1.0000
   6.750   1.2300   0.01585   0.00901  -0.0704   0.2957   1.0000
   7.000   1.2447   0.01595   0.00920  -0.0682   0.2933   1.0000
   7.250   1.2604   0.01611   0.00941  -0.0663   0.2903   1.0000
   7.500   1.2754   0.01627   0.00960  -0.0643   0.2862   1.0000
   7.750   1.2899   0.01657   0.00986  -0.0623   0.2820   1.0000
   8.000   1.3062   0.01681   0.01015  -0.0606   0.2782   1.0000
   8.250   1.3232   0.01700   0.01041  -0.0591   0.2742   1.0000
   8.500   1.3383   0.01727   0.01068  -0.0573   0.2687   1.0000
   8.750   1.3537   0.01759   0.01101  -0.0557   0.2629   1.0000
   9.000   1.3698   0.01786   0.01131  -0.0542   0.2542   1.0000
   9.250   1.3850   0.01822   0.01166  -0.0527   0.2424   1.0000
   9.500   1.3952   0.01886   0.01218  -0.0505   0.2200   1.0000
   9.750   1.3956   0.02010   0.01316  -0.0471   0.1830   1.0000
  10.000   1.3917   0.02171   0.01456  -0.0433   0.1542   1.0000
  10.250   1.3890   0.02334   0.01604  -0.0399   0.1296   1.0000
  10.500   1.3785   0.02553   0.01801  -0.0359   0.0957   1.0000
  10.750   1.3517   0.02899   0.02120  -0.0308   0.0488   1.0000
  11.000   1.3361   0.03195   0.02411  -0.0273   0.0209   1.0000
  11.250   1.3381   0.03373   0.02597  -0.0255   0.0186   1.0000
  11.500   1.3420   0.03544   0.02777  -0.0241   0.0175   1.0000
  11.750   1.3452   0.03729   0.02972  -0.0229   0.0168   1.0000
  12.000   1.3486   0.03922   0.03175  -0.0219   0.0165   1.0000
  12.250   1.3494   0.04148   0.03413  -0.0209   0.0160   1.0000
  12.500   1.3483   0.04404   0.03681  -0.0200   0.0155   1.0000
  12.750   1.3438   0.04708   0.03997  -0.0193   0.0150   1.0000
  13.000   1.3382   0.05037   0.04339  -0.0188   0.0148   1.0000
  13.250   1.3291   0.05414   0.04729  -0.0184   0.0145   1.0000
  13.500   1.3190   0.05816   0.05144  -0.0183   0.0144   1.0000
  13.750   1.3033   0.06306   0.05649  -0.0184   0.0141   1.0000
  14.000   1.2888   0.06802   0.06159  -0.0188   0.0140   1.0000
  14.250   1.2738   0.07327   0.06698  -0.0196   0.0137   1.0000
  14.500   1.2612   0.07838   0.07221  -0.0204   0.0137   1.0000
  14.750   1.2427   0.08443   0.07840  -0.0216   0.0138   1.0000
  15.000   1.2368   0.08863   0.08269  -0.0224   0.0134   1.0000
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