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Glenn Martin 4 (glennmartin4-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: Glenn Martin 4 (glennmartin4-il)
Reynolds number: 1,000,000
Max Cl/Cd: 79.35 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-glennmartin4-il-1000000.txt
Download as CSV file: xf-glennmartin4-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.6898   0.05061   0.04864  -0.1000   0.9616   0.0118
 -12.000  -0.6897   0.04610   0.04402  -0.1005   0.9590   0.0121
 -11.750  -0.7603   0.03681   0.03406  -0.0923   0.9505   0.0120
 -11.500  -0.7621   0.03304   0.02991  -0.0900   0.9486   0.0120
 -11.250  -0.7241   0.03369   0.03069  -0.0915   0.9482   0.0124
 -11.000  -0.7294   0.03161   0.02842  -0.0863   0.9416   0.0124
 -10.750  -0.7174   0.02941   0.02597  -0.0846   0.9397   0.0125
 -10.500  -0.6894   0.02901   0.02555  -0.0849   0.9389   0.0129
 -10.250  -0.6649   0.02764   0.02401  -0.0849   0.9381   0.0131
 -10.000  -0.6591   0.02686   0.02314  -0.0806   0.9318   0.0135
  -9.750  -0.6397   0.02548   0.02158  -0.0794   0.9298   0.0137
  -9.500  -0.6193   0.02407   0.01996  -0.0783   0.9285   0.0140
  -9.250  -0.5888   0.02371   0.01952  -0.0788   0.9277   0.0143
  -9.000  -0.5847   0.02211   0.01772  -0.0744   0.9219   0.0149
  -8.750  -0.5649   0.02103   0.01652  -0.0728   0.9190   0.0150
  -8.500  -0.5372   0.02045   0.01591  -0.0727   0.9175   0.0154
  -8.250  -0.5075   0.01982   0.01522  -0.0730   0.9163   0.0157
  -8.000  -0.4778   0.01941   0.01477  -0.0733   0.9154   0.0163
  -7.750  -0.4687   0.01875   0.01402  -0.0693   0.9083   0.0165
  -7.500  -0.4422   0.01811   0.01330  -0.0689   0.9057   0.0169
  -7.250  -0.4112   0.01763   0.01273  -0.0693   0.9039   0.0176
  -7.000  -0.3853   0.01650   0.01146  -0.0688   0.9024   0.0182
  -6.750  -0.3735   0.01625   0.01122  -0.0652   0.8930   0.0190
  -6.500  -0.3481   0.01546   0.01036  -0.0644   0.8893   0.0191
  -6.250  -0.3277   0.01548   0.01039  -0.0626   0.8813   0.0201
  -5.750  -0.2703   0.01460   0.00936  -0.0625   0.8676   0.0216
  -5.500  -0.2358   0.01355   0.00820  -0.0638   0.8600   0.0226
  -5.250  -0.1951   0.01294   0.00755  -0.0664   0.8473   0.0235
  -5.000  -0.1472   0.01241   0.00693  -0.0707   0.8323   0.0249
  -4.750  -0.1059   0.01199   0.00635  -0.0734   0.8102   0.0259
  -4.500  -0.0790   0.01183   0.00603  -0.0731   0.7817   0.0263
  -4.250  -0.0654   0.01146   0.00547  -0.0699   0.7477   0.0274
  -4.000  -0.0596   0.01155   0.00537  -0.0650   0.6977   0.0291
  -3.750  -0.0524   0.01164   0.00523  -0.0605   0.6522   0.0291
  -3.500  -0.0389   0.01166   0.00508  -0.0573   0.6216   0.0299
  -3.250  -0.0227   0.01169   0.00497  -0.0548   0.5976   0.0309
  -3.000  -0.0019   0.01164   0.00484  -0.0532   0.5840   0.0316
  -2.750   0.0184   0.01153   0.00464  -0.0516   0.5708   0.0326
  -2.500   0.0396   0.01140   0.00444  -0.0501   0.5597   0.0338
  -2.250   0.0609   0.01137   0.00434  -0.0487   0.5472   0.0353
  -2.000   0.0850   0.01127   0.00421  -0.0479   0.5397   0.0366
  -1.750   0.1077   0.01124   0.00411  -0.0468   0.5308   0.0380
  -1.500   0.1321   0.01117   0.00401  -0.0461   0.5220   0.0413
  -1.250   0.1554   0.01117   0.00398  -0.0452   0.5136   0.0442
  -1.000   0.1809   0.01113   0.00404  -0.0448   0.5061   0.0616
  -0.750   0.2043   0.01119   0.00407  -0.0439   0.4979   0.0688
  -0.500   0.2293   0.01122   0.00408  -0.0434   0.4909   0.0737
  -0.250   0.2528   0.01131   0.00412  -0.0426   0.4825   0.0759
   0.000   0.2794   0.01128   0.00407  -0.0425   0.4739   0.0816
   0.250   0.3047   0.01132   0.00407  -0.0421   0.4650   0.0850
   0.500   0.3304   0.01136   0.00407  -0.0419   0.4545   0.0880
   0.750   0.3554   0.01144   0.00408  -0.0415   0.4443   0.0890
   1.000   0.3815   0.01149   0.00409  -0.0413   0.4346   0.0902
   1.250   0.4086   0.01154   0.00412  -0.0415   0.4217   0.0981
   1.500   0.4342   0.01164   0.00417  -0.0412   0.4100   0.0999
   1.750   0.6755   0.01073   0.00552  -0.0917   0.3718   0.9595
   2.000   0.6897   0.01118   0.00590  -0.0888   0.3645   0.9864
   2.250   0.7383   0.01163   0.00625  -0.0939   0.3548   0.9926
   2.500   0.7988   0.01197   0.00650  -0.1017   0.3457   0.9984
   2.750   0.8373   0.01213   0.00659  -0.1045   0.3397   1.0000
   3.000   0.8568   0.01230   0.00670  -0.1031   0.3343   1.0000
   3.250   0.8780   0.01240   0.00679  -0.1020   0.3313   1.0000
   3.500   0.8990   0.01252   0.00689  -0.1008   0.3278   1.0000
   3.750   0.9193   0.01268   0.00700  -0.0996   0.3235   1.0000
   4.000   0.9389   0.01288   0.00716  -0.0983   0.3189   1.0000
   4.250   0.9602   0.01301   0.00728  -0.0972   0.3171   1.0000
   4.500   0.9817   0.01313   0.00741  -0.0963   0.3144   1.0000
   4.750   1.0025   0.01328   0.00755  -0.0952   0.3116   1.0000
   5.000   1.0225   0.01346   0.00771  -0.0940   0.3092   1.0000
   5.250   1.0420   0.01366   0.00790  -0.0926   0.3064   1.0000
   5.500   1.0600   0.01393   0.00813  -0.0911   0.3023   1.0000
   5.750   1.0819   0.01404   0.00826  -0.0903   0.3003   1.0000
   6.000   1.1031   0.01418   0.00842  -0.0893   0.2970   1.0000
   6.250   1.1234   0.01437   0.00863  -0.0882   0.2963   1.0000
   6.500   1.1435   0.01456   0.00882  -0.0871   0.2940   1.0000
   6.750   1.1629   0.01478   0.00904  -0.0859   0.2913   1.0000
   7.000   1.1799   0.01510   0.00933  -0.0843   0.2864   1.0000
   7.250   1.2007   0.01526   0.00952  -0.0834   0.2848   1.0000
   7.500   1.2213   0.01543   0.00972  -0.0825   0.2824   1.0000
   7.750   1.2411   0.01564   0.00995  -0.0814   0.2802   1.0000
   8.000   1.2597   0.01591   0.01020  -0.0802   0.2753   1.0000
   8.250   1.2770   0.01623   0.01051  -0.0788   0.2706   1.0000
   8.500   1.2986   0.01638   0.01070  -0.0781   0.2675   1.0000
   8.750   1.3173   0.01665   0.01097  -0.0769   0.2625   1.0000
   9.000   1.3338   0.01700   0.01131  -0.0754   0.2579   1.0000
   9.250   1.3526   0.01727   0.01161  -0.0743   0.2538   1.0000
   9.500   1.3713   0.01755   0.01188  -0.0733   0.2472   1.0000
   9.750   1.3871   0.01796   0.01227  -0.0717   0.2387   1.0000
  10.000   1.4010   0.01845   0.01271  -0.0699   0.2276   1.0000
  10.250   1.4126   0.01907   0.01325  -0.0678   0.2112   1.0000
  10.500   1.4199   0.01991   0.01398  -0.0649   0.1903   1.0000
  10.750   1.4131   0.02145   0.01530  -0.0600   0.1562   1.0000
  11.000   1.3998   0.02340   0.01703  -0.0543   0.1212   1.0000
  11.250   1.3733   0.02623   0.01960  -0.0471   0.0711   1.0000
  11.500   1.3555   0.02879   0.02209  -0.0417   0.0370   1.0000
  12.000   1.3529   0.03220   0.02548  -0.0360   0.0189   1.0000
  12.250   1.3560   0.03373   0.02706  -0.0339   0.0174   1.0000
  12.500   1.3576   0.03545   0.02886  -0.0318   0.0158   1.0000
  12.750   1.3625   0.03696   0.03043  -0.0303   0.0149   1.0000
  13.000   1.3639   0.03881   0.03236  -0.0287   0.0148   1.0000
  13.250   1.3611   0.04112   0.03473  -0.0269   0.0136   1.0000
  13.500   1.3602   0.04338   0.03708  -0.0255   0.0130   1.0000
  13.750   1.3555   0.04611   0.03992  -0.0241   0.0130   1.0000
  14.000   1.3580   0.04824   0.04210  -0.0234   0.0124   1.0000
  14.250   1.3550   0.05099   0.04495  -0.0226   0.0120   1.0000
  14.500   1.3458   0.05452   0.04861  -0.0218   0.0121   1.0000
  14.750   1.3442   0.05729   0.05144  -0.0214   0.0118   1.0000
  15.000   1.3365   0.06083   0.05507  -0.0211   0.0111   1.0000
  15.250   1.3252   0.06487   0.05923  -0.0208   0.0112   1.0000
  15.500   1.3162   0.06865   0.06309  -0.0208   0.0108   1.0000
  15.750   1.3047   0.07282   0.06739  -0.0207   0.0111   1.0000
  16.000   1.2741   0.07953   0.07424  -0.0209   0.0104   1.0000
  16.250   1.2679   0.08318   0.07797  -0.0212   0.0105   1.0000
  16.500   1.2468   0.08889   0.08382  -0.0217   0.0104   1.0000
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