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Glenn Martin 4 (glennmartin4-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: Glenn Martin 4 (glennmartin4-il)
Reynolds number: 500,000
Max Cl/Cd: 62.85 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-glennmartin4-il-500000-n5.txt
Download as CSV file: xf-glennmartin4-il-500000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.6085   0.04183   0.03881  -0.1010   0.9418   0.0103
 -10.750  -0.6569   0.03417   0.03051  -0.0926   0.9329   0.0101
 -10.500  -0.6403   0.03228   0.02842  -0.0918   0.9314   0.0104
 -10.250  -0.6381   0.03138   0.02746  -0.0871   0.9242   0.0107
 -10.000  -0.6242   0.02958   0.02544  -0.0854   0.9217   0.0108
  -9.750  -0.6030   0.02819   0.02387  -0.0848   0.9200   0.0112
  -9.500  -0.6024   0.02689   0.02237  -0.0798   0.9122   0.0114
  -9.250  -0.5847   0.02551   0.02075  -0.0782   0.9094   0.0121
  -9.000  -0.5644   0.02417   0.01918  -0.0770   0.9075   0.0123
  -8.750  -0.5560   0.02329   0.01816  -0.0732   0.9004   0.0125
  -8.500  -0.5372   0.02237   0.01714  -0.0715   0.8962   0.0129
  -8.250  -0.5101   0.02187   0.01660  -0.0713   0.8937   0.0135
  -8.000  -0.4942   0.02131   0.01596  -0.0688   0.8874   0.0139
  -7.750  -0.4768   0.02063   0.01516  -0.0666   0.8818   0.0142
  -7.500  -0.4543   0.01986   0.01426  -0.0654   0.8783   0.0147
  -7.250  -0.4331   0.01949   0.01378  -0.0639   0.8728   0.0156
  -7.000  -0.4153   0.01880   0.01298  -0.0617   0.8653   0.0160
  -6.750  -0.3879   0.01818   0.01230  -0.0614   0.8613   0.0166
  -6.500  -0.3633   0.01785   0.01194  -0.0606   0.8520   0.0174
  -6.250  -0.3272   0.01718   0.01117  -0.0620   0.8444   0.0185
  -6.000  -0.2922   0.01659   0.01042  -0.0633   0.8342   0.0196
  -5.750  -0.2428   0.01556   0.00926  -0.0677   0.8198   0.0205
  -5.500  -0.1890   0.01496   0.00852  -0.0731   0.7978   0.0222
  -5.250  -0.1489   0.01457   0.00792  -0.0756   0.7718   0.0238
  -5.000  -0.1225   0.01435   0.00744  -0.0751   0.7305   0.0245
  -4.750  -0.1083   0.01424   0.00710  -0.0721   0.6875   0.0255
  -4.500  -0.0978   0.01416   0.00682  -0.0684   0.6506   0.0264
  -4.250  -0.0837   0.01415   0.00665  -0.0654   0.6248   0.0272
  -4.000  -0.0676   0.01406   0.00642  -0.0629   0.6045   0.0281
  -3.750  -0.0493   0.01400   0.00624  -0.0608   0.5895   0.0290
  -3.500  -0.0311   0.01392   0.00605  -0.0587   0.5743   0.0301
  -3.000   0.0079   0.01371   0.00566  -0.0551   0.5519   0.0317
  -2.750   0.0274   0.01357   0.00545  -0.0533   0.5424   0.0336
  -2.500   0.0488   0.01347   0.00530  -0.0520   0.5340   0.0348
  -2.250   0.0697   0.01342   0.00517  -0.0505   0.5258   0.0362
  -2.000   0.0916   0.01336   0.00504  -0.0492   0.5161   0.0373
  -1.750   0.1132   0.01333   0.00495  -0.0480   0.5089   0.0391
  -1.500   0.1362   0.01326   0.00487  -0.0470   0.5004   0.0429
  -1.250   0.1585   0.01325   0.00488  -0.0459   0.4929   0.0502
  -1.000   0.1819   0.01326   0.00489  -0.0451   0.4852   0.0588
  -0.750   0.2043   0.01332   0.00490  -0.0440   0.4769   0.0654
  -0.500   0.2280   0.01334   0.00488  -0.0432   0.4696   0.0692
  -0.250   0.2506   0.01342   0.00489  -0.0422   0.4609   0.0733
   0.000   0.2743   0.01344   0.00487  -0.0415   0.4528   0.0762
   0.250   0.2971   0.01348   0.00487  -0.0407   0.4430   0.0813
   0.500   0.3208   0.01353   0.00487  -0.0399   0.4331   0.0832
   0.750   0.3435   0.01362   0.00488  -0.0391   0.4240   0.0853
   1.000   0.3652   0.01374   0.00493  -0.0381   0.4097   0.0867
   1.250   0.3900   0.01379   0.00496  -0.0377   0.4015   0.0899
   1.500   0.4131   0.01391   0.00503  -0.0370   0.3907   0.0935
   2.000   0.4633   0.01406   0.00522  -0.0366   0.3729   0.1274
   2.250   0.4877   0.01419   0.00532  -0.0363   0.3647   0.1437
   2.750   0.7751   0.01429   0.00749  -0.0909   0.3392   0.9957
   3.000   0.8194   0.01463   0.00775  -0.0951   0.3330   0.9995
   3.250   0.8435   0.01486   0.00792  -0.0947   0.3286   1.0000
   3.500   0.8642   0.01501   0.00804  -0.0936   0.3257   1.0000
   3.750   0.8844   0.01518   0.00819  -0.0924   0.3222   1.0000
   4.000   0.9045   0.01536   0.00835  -0.0912   0.3188   1.0000
   4.250   0.9241   0.01557   0.00852  -0.0899   0.3159   1.0000
   4.500   0.9436   0.01580   0.00871  -0.0886   0.3131   1.0000
   4.750   0.9638   0.01598   0.00889  -0.0875   0.3100   1.0000
   5.000   0.9840   0.01617   0.00909  -0.0863   0.3085   1.0000
   5.250   1.0037   0.01638   0.00930  -0.0851   0.3053   1.0000
   5.500   1.0231   0.01661   0.00953  -0.0839   0.3025   1.0000
   5.750   1.0423   0.01685   0.00976  -0.0827   0.3005   1.0000
   6.000   1.0610   0.01712   0.01002  -0.0813   0.2982   1.0000
   6.250   1.0797   0.01740   0.01029  -0.0801   0.2957   1.0000
   6.500   1.0998   0.01762   0.01054  -0.0790   0.2940   1.0000
   6.750   1.1196   0.01785   0.01079  -0.0780   0.2909   1.0000
   7.000   1.1385   0.01812   0.01109  -0.0768   0.2891   1.0000
   7.250   1.1570   0.01841   0.01139  -0.0755   0.2870   1.0000
   7.500   1.1754   0.01871   0.01171  -0.0743   0.2850   1.0000
   7.750   1.1933   0.01903   0.01205  -0.0730   0.2828   1.0000
   8.000   1.2095   0.01942   0.01244  -0.0715   0.2797   1.0000
   8.250   1.2288   0.01969   0.01277  -0.0705   0.2773   1.0000
   8.500   1.2470   0.01999   0.01311  -0.0693   0.2735   1.0000
   8.750   1.2626   0.02041   0.01351  -0.0678   0.2671   1.0000
   9.000   1.2790   0.02080   0.01392  -0.0664   0.2627   1.0000
   9.250   1.2966   0.02116   0.01434  -0.0652   0.2600   1.0000
   9.500   1.3134   0.02155   0.01477  -0.0639   0.2564   1.0000
   9.750   1.3257   0.02216   0.01534  -0.0620   0.2488   1.0000
  10.000   1.3416   0.02261   0.01581  -0.0607   0.2400   1.0000
  10.250   1.3551   0.02318   0.01640  -0.0590   0.2357   1.0000
  10.500   1.3671   0.02384   0.01706  -0.0572   0.2229   1.0000
  10.750   1.3730   0.02485   0.01797  -0.0546   0.2055   1.0000
  11.000   1.3831   0.02565   0.01878  -0.0526   0.1948   1.0000
  11.250   1.3733   0.02764   0.02055  -0.0481   0.1623   1.0000
  11.500   1.3718   0.02923   0.02207  -0.0450   0.1447   1.0000
  11.750   1.3609   0.03150   0.02423  -0.0409   0.1208   1.0000
  12.000   1.3323   0.03520   0.02773  -0.0354   0.0766   1.0000
  12.250   1.3162   0.03829   0.03078  -0.0318   0.0529   1.0000
  12.500   1.3015   0.04148   0.03402  -0.0289   0.0333   1.0000
  12.750   1.2930   0.04438   0.03694  -0.0269   0.0219   1.0000
  13.000   1.2882   0.04710   0.03971  -0.0255   0.0171   1.0000
  13.250   1.2897   0.04931   0.04203  -0.0246   0.0171   1.0000
  13.500   1.2858   0.05216   0.04497  -0.0237   0.0156   1.0000
  13.750   1.2820   0.05510   0.04801  -0.0230   0.0147   1.0000
  14.000   1.2754   0.05841   0.05142  -0.0224   0.0137   1.0000
  14.250   1.2728   0.06136   0.05447  -0.0221   0.0132   1.0000
  14.500   1.2675   0.06467   0.05789  -0.0218   0.0127   1.0000
  14.750   1.2589   0.06843   0.06177  -0.0216   0.0119   1.0000
  15.000   1.2510   0.07216   0.06561  -0.0215   0.0119   1.0000
  15.250   1.2416   0.07613   0.06969  -0.0215   0.0116   1.0000
  15.500   1.2305   0.08037   0.07404  -0.0217   0.0112   1.0000
  15.750   1.2169   0.08503   0.07881  -0.0220   0.0107   1.0000
  16.000   1.2072   0.08923   0.08312  -0.0224   0.0109   1.0000
  16.250   1.1932   0.09408   0.08808  -0.0230   0.0101   1.0000
  16.500   1.1827   0.09853   0.09263  -0.0236   0.0101   1.0000
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