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Glenn Martin 4 (glennmartin4-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: Glenn Martin 4 (glennmartin4-il)
Reynolds number: 500,000
Max Cl/Cd: 64.89 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-glennmartin4-il-500000.txt
Download as CSV file: xf-glennmartin4-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Glenn Martin 4                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2232   0.09396   0.09185  -0.0703   0.9593   0.0270
  -8.750  -0.2078   0.09033   0.08822  -0.0743   0.9576   0.0273
  -8.500  -0.2016   0.08679   0.08468  -0.0760   0.9513   0.0277
  -8.250  -0.1908   0.08375   0.08164  -0.0790   0.9491   0.0286
  -7.750  -0.3745   0.04432   0.04133  -0.0815   0.9238   0.0219
  -7.500  -0.3714   0.04135   0.03822  -0.0791   0.9179   0.0223
  -7.250  -0.3102   0.04650   0.04358  -0.0834   0.9171   0.0267
  -7.000  -0.2935   0.04374   0.04072  -0.0836   0.9150   0.0271
  -6.750  -0.2880   0.04220   0.03912  -0.0803   0.9058   0.0274
  -6.500  -0.3559   0.02743   0.02287  -0.0647   0.8968   0.0236
  -6.250  -0.3359   0.02568   0.02087  -0.0630   0.8918   0.0248
  -6.000  -0.3097   0.02414   0.01892  -0.0622   0.8893   0.0263
  -5.750  -0.3010   0.02229   0.01674  -0.0581   0.8804   0.0267
  -5.500  -0.2773   0.02051   0.01486  -0.0572   0.8763   0.0277
  -5.250  -0.2476   0.01948   0.01373  -0.0573   0.8735   0.0286
  -5.000  -0.2335   0.01901   0.01320  -0.0542   0.8628   0.0298
  -4.750  -0.2016   0.01790   0.01191  -0.0546   0.8588   0.0309
  -4.500  -0.1795   0.01729   0.01117  -0.0531   0.8480   0.0316
  -4.250  -0.1430   0.01586   0.00962  -0.0547   0.8419   0.0336
  -4.000  -0.1072   0.01519   0.00890  -0.0562   0.8303   0.0360
  -3.750  -0.0618   0.01431   0.00788  -0.0596   0.8156   0.0372
  -3.500  -0.0135   0.01341   0.00682  -0.0638   0.7972   0.0393
  -3.250   0.0239   0.01285   0.00613  -0.0657   0.7682   0.0413
  -3.000   0.0518   0.01270   0.00579  -0.0656   0.7316   0.0435
  -2.750   0.0672   0.01271   0.00555  -0.0628   0.6863   0.0449
  -2.500   0.0791   0.01275   0.00534  -0.0592   0.6496   0.0460
  -2.250   0.0956   0.01269   0.00518  -0.0568   0.6282   0.0483
  -2.000   0.1138   0.01271   0.00510  -0.0547   0.6089   0.0511
  -1.750   0.1335   0.01272   0.00500  -0.0529   0.5937   0.0549
  -1.500   0.1546   0.01279   0.00503  -0.0515   0.5812   0.0615
  -1.250   0.1764   0.01276   0.00497  -0.0502   0.5698   0.0690
  -1.000   0.1985   0.01274   0.00490  -0.0490   0.5593   0.0809
  -0.750   0.2199   0.01277   0.00485  -0.0477   0.5480   0.0872
  -0.500   0.2433   0.01272   0.00477  -0.0469   0.5393   0.0938
  -0.250   0.2662   0.01274   0.00473  -0.0460   0.5305   0.0986
   0.000   0.2897   0.01274   0.00470  -0.0452   0.5211   0.1043
   0.250   0.3131   0.01276   0.00470  -0.0445   0.5121   0.1125
   0.500   0.3372   0.01277   0.00472  -0.0438   0.5029   0.1225
   0.750   0.3613   0.01280   0.00476  -0.0432   0.4940   0.1387
   1.000   0.3909   0.01263   0.00481  -0.0441   0.4842   0.2224
   1.250   0.6926   0.01294   0.00699  -0.1070   0.4458   0.9994
   1.500   0.7163   0.01308   0.00704  -0.1065   0.4338   1.0000
   1.750   0.7341   0.01321   0.00708  -0.1046   0.4222   1.0000
   2.000   0.7516   0.01338   0.00715  -0.1028   0.4116   1.0000
   2.250   0.7695   0.01355   0.00723  -0.1009   0.4007   1.0000
   2.500   0.7886   0.01371   0.00732  -0.0994   0.3920   1.0000
   2.750   0.8071   0.01392   0.00744  -0.0978   0.3842   1.0000
   3.000   0.8270   0.01408   0.00755  -0.0965   0.3776   1.0000
   3.250   0.8461   0.01428   0.00768  -0.0950   0.3702   1.0000
   3.500   0.8656   0.01449   0.00783  -0.0936   0.3651   1.0000
   3.750   0.8861   0.01465   0.00797  -0.0924   0.3599   1.0000
   4.000   0.9056   0.01486   0.00813  -0.0911   0.3548   1.0000
   4.250   0.9247   0.01513   0.00832  -0.0896   0.3504   1.0000
   4.500   0.9455   0.01528   0.00849  -0.0886   0.3462   1.0000
   4.750   0.9658   0.01548   0.00868  -0.0874   0.3433   1.0000
   5.000   0.9848   0.01572   0.00888  -0.0860   0.3389   1.0000
   5.250   1.0041   0.01599   0.00911  -0.0847   0.3356   1.0000
   5.500   1.0245   0.01622   0.00934  -0.0837   0.3325   1.0000
   5.750   1.0451   0.01641   0.00956  -0.0826   0.3301   1.0000
   6.000   1.0653   0.01663   0.00978  -0.0816   0.3273   1.0000
   6.250   1.0849   0.01688   0.01003  -0.0804   0.3241   1.0000
   6.500   1.1041   0.01717   0.01029  -0.0792   0.3209   1.0000
   6.750   1.1238   0.01747   0.01058  -0.0781   0.3174   1.0000
   7.000   1.1439   0.01770   0.01086  -0.0771   0.3157   1.0000
   7.250   1.1630   0.01795   0.01114  -0.0759   0.3129   1.0000
   7.500   1.1816   0.01821   0.01143  -0.0747   0.3101   1.0000
   7.750   1.2003   0.01851   0.01173  -0.0735   0.3074   1.0000
   8.000   1.2178   0.01892   0.01209  -0.0721   0.3023   1.0000
   8.250   1.2353   0.01917   0.01242  -0.0707   0.2996   1.0000
   8.500   1.2523   0.01945   0.01275  -0.0693   0.2959   1.0000
   8.750   1.2695   0.01977   0.01311  -0.0679   0.2929   1.0000
   9.000   1.2845   0.02020   0.01351  -0.0662   0.2884   1.0000
   9.250   1.3017   0.02056   0.01392  -0.0649   0.2853   1.0000
   9.500   1.3178   0.02087   0.01431  -0.0634   0.2811   1.0000
   9.750   1.3335   0.02125   0.01473  -0.0619   0.2771   1.0000
  10.000   1.3453   0.02181   0.01526  -0.0598   0.2708   1.0000
  10.250   1.3627   0.02217   0.01571  -0.0586   0.2688   1.0000
  10.500   1.3776   0.02258   0.01618  -0.0571   0.2612   1.0000
  10.750   1.3898   0.02315   0.01674  -0.0553   0.2518   1.0000
  11.000   1.4015   0.02378   0.01738  -0.0534   0.2428   1.0000
  11.250   1.4111   0.02455   0.01812  -0.0513   0.2278   1.0000
  11.500   1.4172   0.02556   0.01906  -0.0487   0.2078   1.0000
  11.750   1.4111   0.02731   0.02063  -0.0448   0.1767   1.0000
  12.000   1.3904   0.03008   0.02315  -0.0393   0.1389   1.0000
  12.250   1.3691   0.03311   0.02601  -0.0343   0.1078   1.0000
  12.500   1.3204   0.03856   0.03123  -0.0276   0.0484   1.0000
  12.750   1.3113   0.04133   0.03406  -0.0252   0.0367   1.0000
  13.000   1.3036   0.04415   0.03694  -0.0233   0.0296   1.0000
  13.250   1.2970   0.04706   0.03992  -0.0217   0.0255   1.0000
  13.500   1.2927   0.04988   0.04285  -0.0206   0.0236   1.0000
  13.750   1.2853   0.05314   0.04622  -0.0197   0.0222   1.0000
  14.000   1.2773   0.05658   0.04977  -0.0191   0.0213   1.0000
  14.250   1.2685   0.06023   0.05355  -0.0186   0.0206   1.0000
  14.500   1.2591   0.06403   0.05748  -0.0183   0.0201   1.0000
  14.750   1.2498   0.06791   0.06148  -0.0181   0.0199   1.0000
  15.000   1.2382   0.07211   0.06579  -0.0181   0.0191   1.0000
  15.250   1.2263   0.07641   0.07022  -0.0182   0.0188   1.0000
  15.500   1.2147   0.08074   0.07465  -0.0184   0.0184   1.0000
  15.750   1.2008   0.08553   0.07956  -0.0188   0.0185   1.0000
  16.000   1.1797   0.09135   0.08551  -0.0194   0.0178   1.0000
  16.250   1.1709   0.09555   0.08981  -0.0200   0.0178   1.0000
  16.500   1.1534   0.10106   0.09544  -0.0209   0.0176   1.0000
  16.750   1.1339   0.10697   0.10146  -0.0219   0.0171   1.0000
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