Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

Glenn Martin 4 (glennmartin4-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: Glenn Martin 4 (glennmartin4-il)
Reynolds number: 200,000
Max Cl/Cd: 54.65 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-glennmartin4-il-200000.txt
Download as CSV file: xf-glennmartin4-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -5.750  -0.2696   0.06271   0.05925  -0.0640   0.9066   0.0675
  -5.500  -0.2428   0.05881   0.05520  -0.0661   0.9022   0.0706
  -5.250  -0.2402   0.05620   0.05173  -0.0625   0.8892   0.0761
  -5.000  -0.2344   0.05013   0.04572  -0.0609   0.8794   0.0773
  -4.750  -0.2075   0.04639   0.04195  -0.0617   0.8749   0.0788
  -4.500  -0.1938   0.04380   0.03923  -0.0595   0.8639   0.0800
  -4.250  -0.1688   0.04078   0.03600  -0.0591   0.8596   0.0839
  -4.000  -0.1881   0.03134   0.02484  -0.0460   0.8476   0.0541
  -3.750  -0.1613   0.02855   0.02161  -0.0450   0.8440   0.0545
  -3.500  -0.1405   0.02729   0.02050  -0.0438   0.8326   0.0575
  -3.250  -0.1061   0.02508   0.01797  -0.0441   0.8281   0.0585
  -3.000  -0.0810   0.02366   0.01629  -0.0427   0.8158   0.0609
  -2.750  -0.0456   0.02241   0.01470  -0.0433   0.8058   0.0637
  -2.500   0.0025   0.02042   0.01254  -0.0468   0.7962   0.0666
  -2.250   0.0478   0.01927   0.01128  -0.0500   0.7807   0.0706
  -2.000   0.0992   0.01834   0.01009  -0.0542   0.7625   0.0762
  -1.750   0.1460   0.01699   0.00873  -0.0581   0.7389   0.0840
  -1.500   0.1922   0.01607   0.00770  -0.0618   0.7144   0.0980
  -1.250   0.2254   0.01557   0.00709  -0.0628   0.6892   0.1150
  -1.000   0.2567   0.01538   0.00674  -0.0635   0.6668   0.1323
  -0.750   0.2854   0.01526   0.00651  -0.0637   0.6490   0.1459
  -0.500   0.3112   0.01518   0.00632  -0.0634   0.6319   0.1620
  -0.250   0.3350   0.01509   0.00620  -0.0626   0.6169   0.1854
   0.000   0.6551   0.01533   0.00827  -0.1270   0.5749   1.0000
   0.250   0.6735   0.01548   0.00823  -0.1254   0.5623   1.0000
   0.500   0.6893   0.01561   0.00822  -0.1232   0.5499   1.0000
   0.750   0.7048   0.01575   0.00825  -0.1209   0.5377   1.0000
   1.000   0.7232   0.01592   0.00827  -0.1192   0.5265   1.0000
   1.250   0.7398   0.01610   0.00830  -0.1171   0.5149   1.0000
   1.500   0.7550   0.01627   0.00839  -0.1147   0.5033   1.0000
   1.750   0.7727   0.01647   0.00846  -0.1129   0.4922   1.0000
   2.000   0.7892   0.01667   0.00854  -0.1108   0.4815   1.0000
   2.250   0.8050   0.01686   0.00866  -0.1085   0.4707   1.0000
   2.500   0.8258   0.01710   0.00876  -0.1074   0.4622   1.0000
   2.750   0.8416   0.01728   0.00892  -0.1051   0.4527   1.0000
   3.000   0.8632   0.01754   0.00903  -0.1042   0.4453   1.0000
   3.250   0.8806   0.01774   0.00923  -0.1023   0.4372   1.0000
   3.500   0.9041   0.01802   0.00934  -0.1018   0.4307   1.0000
   3.750   0.9220   0.01824   0.00958  -0.1001   0.4237   1.0000
   4.000   0.9421   0.01848   0.00976  -0.0989   0.4176   1.0000
   4.250   0.9642   0.01876   0.00997  -0.0981   0.4116   1.0000
   4.500   0.9836   0.01901   0.01022  -0.0967   0.4059   1.0000
   4.750   1.0061   0.01928   0.01042  -0.0961   0.4011   1.0000
   5.000   1.0309   0.01961   0.01068  -0.0959   0.3964   1.0000
   5.250   1.0501   0.01988   0.01100  -0.0946   0.3917   1.0000
   5.500   1.0707   0.02016   0.01125  -0.0935   0.3868   1.0000
   5.750   1.0999   0.02051   0.01150  -0.0944   0.3830   1.0000
   6.000   1.1199   0.02084   0.01190  -0.0933   0.3793   1.0000
   6.250   1.1395   0.02116   0.01226  -0.0921   0.3752   1.0000
   6.500   1.1616   0.02149   0.01258  -0.0914   0.3714   1.0000
   6.750   1.1897   0.02186   0.01288  -0.0921   0.3673   1.0000
   7.000   1.2131   0.02227   0.01335  -0.0918   0.3644   1.0000
   7.250   1.2283   0.02263   0.01380  -0.0898   0.3607   1.0000
   7.500   1.2484   0.02299   0.01422  -0.0889   0.3572   1.0000
   7.750   1.2715   0.02335   0.01456  -0.0885   0.3536   1.0000
   8.000   1.3040   0.02386   0.01501  -0.0903   0.3499   1.0000
   8.250   1.3138   0.02426   0.01557  -0.0872   0.3468   1.0000
   8.500   1.3299   0.02469   0.01611  -0.0855   0.3437   1.0000
   8.750   1.3476   0.02507   0.01654  -0.0841   0.3399   1.0000
   9.000   1.3739   0.02546   0.01687  -0.0846   0.3357   1.0000
   9.250   1.3777   0.02587   0.01740  -0.0805   0.3309   1.0000
   9.500   1.3841   0.02626   0.01790  -0.0770   0.3265   1.0000
   9.750   1.3968   0.02653   0.01816  -0.0747   0.3213   1.0000
  10.000   1.4051   0.02698   0.01865  -0.0717   0.3158   1.0000
  10.250   1.4092   0.02746   0.01927  -0.0679   0.3118   1.0000
  10.500   1.4167   0.02782   0.01968  -0.0649   0.3067   1.0000
  10.750   1.4296   0.02826   0.02009  -0.0630   0.3013   1.0000
  11.000   1.4242   0.02889   0.02093  -0.0577   0.2962   1.0000
  11.250   1.4249   0.02939   0.02149  -0.0538   0.2903   1.0000
  11.500   1.4259   0.03004   0.02218  -0.0500   0.2841   1.0000
  11.750   1.4254   0.03084   0.02314  -0.0462   0.2787   1.0000
  12.000   1.4263   0.03160   0.02389  -0.0429   0.2721   1.0000
  12.250   1.4219   0.03272   0.02521  -0.0390   0.2648   1.0000
  12.500   1.4145   0.03404   0.02658  -0.0349   0.2546   1.0000
  12.750   1.4111   0.03547   0.02815  -0.0318   0.2440   1.0000
  13.000   1.4010   0.03750   0.03020  -0.0283   0.2273   1.0000
  13.250   1.3842   0.04037   0.03301  -0.0248   0.1990   1.0000
  13.500   1.3601   0.04418   0.03667  -0.0214   0.1682   1.0000
  13.750   1.3308   0.04890   0.04126  -0.0185   0.1414   1.0000
  14.000   1.3083   0.05338   0.04570  -0.0167   0.1224   1.0000
  14.250   1.2795   0.05885   0.05112  -0.0154   0.1001   1.0000
  14.500   1.2483   0.06495   0.05720  -0.0146   0.0667   1.0000
  14.750   1.2195   0.07106   0.06334  -0.0144   0.0577   1.0000
  15.000   1.1949   0.07690   0.06925  -0.0145   0.0526   1.0000
  15.250   1.1744   0.08240   0.07488  -0.0147   0.0484   1.0000
  15.500   1.1575   0.08757   0.08019  -0.0152   0.0461   1.0000
  15.750   1.1409   0.09283   0.08559  -0.0158   0.0445   1.0000
<< Back to Glenn Martin 4 (glennmartin4-il)

Polar data table (+)

Polar graphs


<< Back to Glenn Martin 4 (glennmartin4-il)