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 3 (glennmartin3-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: Glenn Martin 3 (glennmartin3-il)
Reynolds number: 100,000
Max Cl/Cd: 41.62 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-glennmartin3-il-100000.txt
Download as CSV file: xf-glennmartin3-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Glenn Martin 3                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -6.500  -0.5521   0.08829   0.08428  -0.0021   1.0000   0.1264
  -6.250  -0.5617   0.08585   0.08181   0.0004   1.0000   0.1302
  -6.000  -0.6114   0.08549   0.08091   0.0039   1.0000   0.1357
  -5.750  -0.5933   0.07966   0.07541   0.0054   1.0000   0.1379
  -5.500  -0.5882   0.07724   0.07306   0.0084   1.0000   0.1406
  -5.250  -0.5894   0.07505   0.07084   0.0113   1.0000   0.1454
  -5.000  -0.6091   0.07288   0.06828   0.0149   1.0000   0.1531
  -4.750  -0.6014   0.06973   0.06529   0.0176   1.0000   0.1558
  -4.500  -0.5982   0.06773   0.06329   0.0207   1.0000   0.1604
  -4.250  -0.6064   0.06547   0.06082   0.0247   1.0000   0.1719
  -4.000  -0.5827   0.06375   0.05908   0.0243   0.9945   0.1810
  -3.750  -0.5383   0.06105   0.05596   0.0193   0.9684   0.2061
  -3.500  -0.5143   0.05878   0.05352   0.0194   0.9534   0.2237
  -3.250  -0.4871   0.05590   0.05071   0.0191   0.9441   0.2323
  -3.000  -0.4820   0.04559   0.03810   0.0283   0.9351   0.1085
  -2.750  -0.4579   0.04304   0.03517   0.0300   0.9253   0.1010
  -2.500  -0.4285   0.04012   0.03146   0.0315   0.9162   0.0955
  -2.250  -0.3897   0.03875   0.02982   0.0299   0.9078   0.0971
  -2.000  -0.3558   0.03726   0.02797   0.0294   0.8975   0.0971
  -1.750  -0.3008   0.03601   0.02647   0.0248   0.8907   0.0996
  -1.500  -0.2582   0.03498   0.02527   0.0223   0.8803   0.1036
  -1.250   0.1777   0.03122   0.02515  -0.0612   0.9038   1.0000
  -1.000   0.2323   0.03047   0.02403  -0.0655   0.8926   1.0000
  -0.750   0.2752   0.02965   0.02297  -0.0676   0.8789   1.0000
  -0.500   0.3135   0.02894   0.02209  -0.0690   0.8659   1.0000
  -0.250   0.3543   0.02818   0.02118  -0.0707   0.8544   1.0000
   0.000   0.4061   0.02709   0.01993  -0.0743   0.8462   1.0000
   0.250   0.4417   0.02621   0.01897  -0.0748   0.8324   1.0000
   0.500   0.4804   0.02520   0.01787  -0.0758   0.8197   1.0000
   0.750   0.5360   0.02354   0.01611  -0.0795   0.8120   1.0000
   1.000   0.5744   0.02242   0.01492  -0.0803   0.7955   1.0000
   1.250   0.6070   0.02154   0.01399  -0.0802   0.7733   1.0000
   1.500   0.6453   0.02057   0.01292  -0.0810   0.7441   1.0000
   1.750   0.6816   0.01981   0.01198  -0.0816   0.6984   1.0000
   2.000   0.7549   0.01882   0.01041  -0.0897   0.6240   1.0000
   2.250   0.7931   0.01910   0.01013  -0.0915   0.5604   1.0000
   2.500   0.8162   0.01961   0.01023  -0.0906   0.5163   1.0000
   2.750   0.8383   0.02018   0.01044  -0.0896   0.4828   1.0000
   3.000   0.8632   0.02084   0.01075  -0.0892   0.4547   1.0000
   3.250   0.8891   0.02155   0.01120  -0.0891   0.4293   1.0000
   3.500   0.9164   0.02224   0.01168  -0.0894   0.4094   1.0000
   3.750   0.9433   0.02293   0.01218  -0.0896   0.3922   1.0000
   4.000   0.9707   0.02360   0.01271  -0.0899   0.3778   1.0000
   4.250   0.9949   0.02417   0.01316  -0.0895   0.3658   1.0000
   4.500   1.0185   0.02477   0.01375  -0.0890   0.3557   1.0000
   4.750   1.0547   0.02554   0.01433  -0.0913   0.3463   1.0000
   5.000   1.0715   0.02605   0.01495  -0.0893   0.3386   1.0000
   5.250   1.1019   0.02671   0.01551  -0.0904   0.3318   1.0000
   5.500   1.1276   0.02742   0.01624  -0.0904   0.3251   1.0000
   5.750   1.1488   0.02802   0.01691  -0.0894   0.3191   1.0000
   6.000   1.1825   0.02876   0.01750  -0.0913   0.3131   1.0000
   6.250   1.2027   0.02950   0.01837  -0.0902   0.3087   1.0000
   6.500   1.2221   0.03022   0.01922  -0.0889   0.3043   1.0000
   6.750   1.2468   0.03095   0.01996  -0.0888   0.3001   1.0000
   7.000   1.2807   0.03184   0.02079  -0.0908   0.2966   1.0000
   7.250   1.3009   0.03281   0.02192  -0.0898   0.2935   1.0000
   7.500   1.3145   0.03369   0.02300  -0.0875   0.2902   1.0000
   7.750   1.3300   0.03452   0.02395  -0.0856   0.2866   1.0000
   8.000   1.3509   0.03541   0.02492  -0.0848   0.2835   1.0000
   8.250   1.3797   0.03638   0.02587  -0.0858   0.2804   1.0000
   8.500   1.3999   0.03765   0.02727  -0.0851   0.2782   1.0000
   8.750   1.4037   0.03887   0.02877  -0.0811   0.2762   1.0000
   9.000   1.4087   0.04017   0.03030  -0.0774   0.2740   1.0000
   9.250   1.4151   0.04150   0.03185  -0.0740   0.2719   1.0000
   9.500   1.4251   0.04269   0.03319  -0.0714   0.2693   1.0000
   9.750   1.4401   0.04383   0.03443  -0.0698   0.2668   1.0000
  10.000   1.4616   0.04505   0.03568  -0.0696   0.2645   1.0000
  10.250   1.4796   0.04680   0.03754  -0.0689   0.2623   1.0000
  10.500   1.4580   0.04849   0.03955  -0.0607   0.2608   1.0000
  10.750   1.4343   0.05012   0.04144  -0.0524   0.2593   1.0000
  11.000   1.4113   0.05225   0.04382  -0.0448   0.2582   1.0000
  11.250   1.3837   0.05455   0.04637  -0.0371   0.2564   1.0000
  11.500   1.3533   0.05748   0.04952  -0.0299   0.2552   1.0000
  11.750   1.3124   0.06130   0.05358  -0.0224   0.2540   1.0000
  12.000   0.9084   0.11398   0.10671  -0.0186   0.2628   1.0000
  12.250   0.7692   0.14674   0.13954  -0.0328   0.3133   1.0000
  12.500   1.3866   0.06491   0.05728  -0.0236   0.2463   1.0000
  12.750   1.3122   0.07113   0.06376  -0.0143   0.2461   1.0000
<< Back to Glenn Martin 3 (glennmartin3-il)

Polar data table (+)

Polar graphs


<< Back to Glenn Martin 3 (glennmartin3-il)