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Glenn Martin 2 (glennmartin2-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: Glenn Martin 2 (glennmartin2-il)
Reynolds number: 200,000
Max Cl/Cd: 57.9 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-glennmartin2-il-200000-n5.txt
Download as CSV file: xf-glennmartin2-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.1180   0.09102   0.08757  -0.0777   0.9531   0.0212
 -10.000  -0.1103   0.08612   0.08268  -0.0820   0.9498   0.0215
  -9.750  -0.1101   0.08185   0.07842  -0.0844   0.9413   0.0218
  -9.500  -0.1052   0.07652   0.07310  -0.0893   0.9366   0.0220
  -9.250  -0.1123   0.07073   0.06733  -0.0938   0.9277   0.0225
  -8.750  -0.2622   0.03165   0.02694  -0.1075   0.8984   0.0241
  -8.500  -0.2307   0.03148   0.02682  -0.1084   0.8924   0.0250
  -8.250  -0.2034   0.02960   0.02469  -0.1096   0.8875   0.0264
  -8.000  -0.1998   0.02703   0.02168  -0.1062   0.8773   0.0275
  -7.750  -0.1784   0.02421   0.01819  -0.1059   0.8720   0.0296
  -7.500  -0.1654   0.02322   0.01707  -0.1033   0.8621   0.0308
  -7.250  -0.1320   0.02261   0.01638  -0.1045   0.8562   0.0325
  -7.000  -0.1155   0.02170   0.01526  -0.1022   0.8457   0.0340
  -6.750  -0.0906   0.02056   0.01378  -0.1016   0.8373   0.0361
  -6.500  -0.0666   0.01964   0.01265  -0.1008   0.8280   0.0380
  -6.250  -0.0433   0.01917   0.01211  -0.0998   0.8173   0.0397
  -6.000  -0.0156   0.01863   0.01142  -0.0996   0.8071   0.0418
  -5.750   0.0105   0.01798   0.01055  -0.0991   0.7948   0.0442
  -5.500   0.0351   0.01728   0.00965  -0.0982   0.7805   0.0458
  -5.250   0.0604   0.01682   0.00913  -0.0975   0.7655   0.0479
  -5.000   0.0871   0.01651   0.00870  -0.0970   0.7489   0.0505
  -4.750   0.1139   0.01608   0.00809  -0.0966   0.7301   0.0530
  -4.500   0.1402   0.01566   0.00746  -0.0959   0.7104   0.0552
  -4.250   0.1654   0.01534   0.00704  -0.0952   0.6908   0.0581
  -4.000   0.1902   0.01521   0.00675  -0.0944   0.6726   0.0621
  -3.750   0.2142   0.01507   0.00639  -0.0934   0.6560   0.0663
  -3.500   0.2367   0.01483   0.00608  -0.0921   0.6418   0.0707
  -3.250   0.2596   0.01473   0.00586  -0.0910   0.6288   0.0761
  -3.000   0.2824   0.01467   0.00564  -0.0898   0.6158   0.0811
  -2.750   0.3039   0.01451   0.00543  -0.0884   0.6034   0.0876
  -2.500   0.3254   0.01446   0.00528  -0.0870   0.5898   0.0937
  -2.250   0.3460   0.01436   0.00512  -0.0854   0.5749   0.0992
  -2.000   0.3654   0.01427   0.00498  -0.0836   0.5570   0.1060
  -1.750   0.3841   0.01424   0.00486  -0.0816   0.5320   0.1133
  -1.500   0.3981   0.01423   0.00475  -0.0788   0.4932   0.1236
  -1.250   0.4086   0.01436   0.00469  -0.0752   0.4565   0.1346
  -0.750   0.4350   0.01462   0.00485  -0.0693   0.4181   0.1892
  -0.500   0.4513   0.01477   0.00495  -0.0670   0.4066   0.2181
  -0.250   0.4684   0.01496   0.00505  -0.0648   0.3977   0.2377
   0.000   0.4871   0.01510   0.00513  -0.0630   0.3902   0.2524
   0.250   0.5048   0.01527   0.00522  -0.0610   0.3840   0.2632
   0.500   0.5251   0.01538   0.00530  -0.0595   0.3789   0.2738
   0.750   0.5451   0.01553   0.00539  -0.0580   0.3738   0.2851
   1.000   0.5643   0.01566   0.00548  -0.0564   0.3695   0.2933
   1.250   0.5842   0.01581   0.00558  -0.0549   0.3660   0.3034
   1.750   0.6250   0.01599   0.00579  -0.0522   0.3590   0.3278
   2.000   0.6450   0.01609   0.00592  -0.0508   0.3558   0.3448
   2.250   0.6637   0.01605   0.00607  -0.0492   0.3530   0.4123
   3.250   0.9488   0.01715   0.00805  -0.0885   0.3370   1.0000
   3.500   0.9677   0.01742   0.00826  -0.0870   0.3351   1.0000
   3.750   0.9879   0.01771   0.00848  -0.0857   0.3333   1.0000
   4.000   1.0064   0.01791   0.00870  -0.0841   0.3315   1.0000
   4.250   1.0255   0.01813   0.00893  -0.0826   0.3298   1.0000
   4.500   1.0446   0.01837   0.00919  -0.0812   0.3279   1.0000
   4.750   1.0639   0.01862   0.00944  -0.0798   0.3262   1.0000
   5.000   1.0821   0.01887   0.00969  -0.0782   0.3239   1.0000
   5.250   1.1002   0.01913   0.00994  -0.0766   0.3217   1.0000
   5.500   1.1188   0.01943   0.01021  -0.0752   0.3191   1.0000
   5.750   1.1403   0.01978   0.01051  -0.0744   0.3168   1.0000
   6.000   1.1555   0.02001   0.01082  -0.0723   0.3143   1.0000
   6.250   1.1721   0.02026   0.01114  -0.0705   0.3118   1.0000
   6.500   1.1884   0.02053   0.01145  -0.0687   0.3089   1.0000
   6.750   1.2054   0.02082   0.01177  -0.0671   0.3064   1.0000
   7.000   1.2229   0.02114   0.01210  -0.0656   0.3040   1.0000
   7.250   1.2420   0.02149   0.01245  -0.0645   0.3017   1.0000
   7.500   1.2588   0.02183   0.01284  -0.0629   0.2992   1.0000
   7.750   1.2694   0.02211   0.01323  -0.0603   0.2948   1.0000
   8.000   1.2799   0.02241   0.01359  -0.0577   0.2898   1.0000
   8.250   1.2900   0.02280   0.01393  -0.0552   0.2844   1.0000
   8.500   1.3016   0.02316   0.01444  -0.0530   0.2791   1.0000
   8.750   1.3135   0.02357   0.01491  -0.0509   0.2742   1.0000
   9.000   1.3241   0.02407   0.01539  -0.0487   0.2694   1.0000
   9.250   1.3370   0.02451   0.01598  -0.0469   0.2628   1.0000
   9.500   1.3468   0.02508   0.01658  -0.0448   0.2565   1.0000
   9.750   1.3560   0.02570   0.01729  -0.0428   0.2450   1.0000
  10.000   1.3642   0.02645   0.01805  -0.0407   0.2312   1.0000
  10.250   1.3685   0.02748   0.01902  -0.0383   0.2110   1.0000
  10.500   1.3662   0.02902   0.02041  -0.0355   0.1852   1.0000
  10.750   1.3613   0.03093   0.02218  -0.0326   0.1645   1.0000
  11.000   1.3529   0.03327   0.02440  -0.0298   0.1448   1.0000
  11.250   1.3455   0.03569   0.02675  -0.0273   0.1243   1.0000
  11.500   1.3289   0.03904   0.02996  -0.0247   0.0968   1.0000
  11.750   1.3068   0.04318   0.03397  -0.0224   0.0661   1.0000
  12.000   1.2849   0.04771   0.03846  -0.0208   0.0418   1.0000
  12.250   1.2642   0.05248   0.04325  -0.0198   0.0234   1.0000
  12.500   1.2546   0.05628   0.04717  -0.0194   0.0202   1.0000
  12.750   1.2472   0.05997   0.05098  -0.0192   0.0190   1.0000
  13.000   1.2395   0.06381   0.05495  -0.0192   0.0181   1.0000
  13.250   1.2313   0.06786   0.05915  -0.0194   0.0174   1.0000
  13.500   1.2232   0.07205   0.06349  -0.0198   0.0168   1.0000
  13.750   1.2157   0.07627   0.06785  -0.0204   0.0167   1.0000
  14.000   1.2045   0.08115   0.07289  -0.0212   0.0159   1.0000
  14.250   1.1945   0.08594   0.07783  -0.0222   0.0155   1.0000
  14.500   1.1868   0.09046   0.08249  -0.0231   0.0156   1.0000
  14.750   1.1757   0.09549   0.08766  -0.0242   0.0150   1.0000
  15.000   1.1654   0.10046   0.09277  -0.0253   0.0148   1.0000
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