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WORTMANN FX M2 AIRFOIL (fxm2-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX M2 AIRFOIL (fxm2-il)
Reynolds number: 50,000
Max Cl/Cd: 35.69 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fxm2-il-50000-n5.txt
Download as CSV file: xf-fxm2-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX M2 AIRFOIL                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2857   0.10769   0.10090  -0.0170   1.0000   0.0741
  -7.750  -0.2929   0.10695   0.10032  -0.0179   1.0000   0.0750
  -7.500  -0.3007   0.10608   0.09958  -0.0191   1.0000   0.0753
  -7.250  -0.2809   0.10014   0.09368  -0.0162   1.0000   0.0777
  -7.000  -0.2774   0.09757   0.09120  -0.0153   1.0000   0.0799
  -6.750  -0.2772   0.09539   0.08914  -0.0150   1.0000   0.0824
  -6.500  -0.2776   0.09350   0.08736  -0.0166   1.0000   0.0850
  -6.250  -0.2774   0.09215   0.08611  -0.0216   1.0000   0.0865
  -6.000  -0.2720   0.08864   0.08271  -0.0209   1.0000   0.0878
  -5.750  -0.2656   0.08536   0.07953  -0.0180   1.0000   0.0907
  -5.500  -0.2598   0.08283   0.07708  -0.0185   1.0000   0.0943
  -5.000  -0.2442   0.07735   0.07173  -0.0235   1.0000   0.1015
  -4.750  -0.2373   0.07467   0.06913  -0.0222   1.0000   0.1060
  -4.250  -0.2151   0.06909   0.06365  -0.0257   1.0000   0.1182
  -4.000  -0.1956   0.06647   0.06098  -0.0310   1.0000   0.1305
  -3.750  -0.1911   0.06392   0.05858  -0.0278   1.0000   0.1374
  -3.500  -0.1483   0.06036   0.05489  -0.0374   0.9920   0.1651
  -3.250  -0.1126   0.05634   0.05094  -0.0408   0.9791   0.1861
  -3.000  -0.0749   0.05294   0.04756  -0.0452   0.9644   0.2219
  -2.500   0.0701   0.04301   0.03646  -0.0695   0.9340   0.1258
  -2.250   0.1315   0.03861   0.03129  -0.0758   0.9169   0.0858
  -2.000   0.1828   0.03550   0.02758  -0.0799   0.8972   0.0752
  -1.750   0.2271   0.03265   0.02456  -0.0831   0.8757   0.0726
  -1.500   0.2707   0.03059   0.02209  -0.0856   0.8489   0.0735
  -1.250   0.3161   0.02874   0.01976  -0.0880   0.8212   0.0744
  -1.000   0.3600   0.02697   0.01761  -0.0899   0.7878   0.0739
  -0.750   0.4025   0.02559   0.01574  -0.0912   0.7474   0.0743
  -0.500   0.4397   0.02448   0.01424  -0.0918   0.7045   0.0779
  -0.250   0.4710   0.02378   0.01314  -0.0911   0.6623   0.0802
   0.000   0.4984   0.02332   0.01226  -0.0898   0.6215   0.0815
   0.250   0.5249   0.02305   0.01155  -0.0885   0.5856   0.0837
   0.500   0.5500   0.02285   0.01102  -0.0872   0.5512   0.0883
   0.750   0.5754   0.02269   0.01062  -0.0862   0.5218   0.0929
   1.000   0.6011   0.02264   0.01033  -0.0854   0.4932   0.0966
   1.250   0.6279   0.02267   0.01008  -0.0848   0.4707   0.1026
   1.500   0.6551   0.02274   0.01003  -0.0845   0.4475   0.1146
   1.750   0.6829   0.02280   0.00999  -0.0842   0.4288   0.1325
   2.000   0.7004   0.02101   0.01009  -0.0818   0.4154   1.0000
   2.250   0.7282   0.02157   0.01018  -0.0813   0.4010   1.0000
   2.500   0.7558   0.02212   0.01044  -0.0810   0.3864   1.0000
   2.750   0.7831   0.02265   0.01074  -0.0807   0.3730   1.0000
   3.000   0.8100   0.02319   0.01104  -0.0804   0.3615   1.0000
   3.250   0.8368   0.02377   0.01138  -0.0800   0.3516   1.0000
   3.500   0.8638   0.02440   0.01178  -0.0798   0.3429   1.0000
   3.750   0.8907   0.02509   0.01241  -0.0795   0.3338   1.0000
   4.000   0.9174   0.02580   0.01302  -0.0793   0.3264   1.0000
   4.250   0.9436   0.02651   0.01369  -0.0790   0.3185   1.0000
   4.500   0.9693   0.02723   0.01442  -0.0786   0.3110   1.0000
   4.750   0.9950   0.02788   0.01494  -0.0782   0.3043   1.0000
   5.000   1.0200   0.02863   0.01570  -0.0777   0.2971   1.0000
   5.250   1.0458   0.02932   0.01621  -0.0774   0.2915   1.0000
   5.500   1.0699   0.03022   0.01720  -0.0769   0.2844   1.0000
   5.750   1.0953   0.03100   0.01787  -0.0765   0.2786   1.0000
   6.000   1.1177   0.03201   0.01907  -0.0759   0.2713   1.0000
   6.250   1.1409   0.03291   0.02000  -0.0753   0.2648   1.0000
   6.500   1.1630   0.03379   0.02098  -0.0746   0.2576   1.0000
   6.750   1.1845   0.03476   0.02210  -0.0739   0.2510   1.0000
   7.000   1.2078   0.03546   0.02276  -0.0733   0.2453   1.0000
   7.250   1.2283   0.03647   0.02390  -0.0725   0.2387   1.0000
   7.500   1.2524   0.03704   0.02432  -0.0720   0.2335   1.0000
   7.750   1.2704   0.03831   0.02582  -0.0710   0.2266   1.0000
   8.000   1.2943   0.03911   0.02654  -0.0705   0.2219   1.0000
   8.250   1.3085   0.04093   0.02876  -0.0694   0.2160   1.0000
   8.500   1.3285   0.04221   0.03013  -0.0686   0.2116   1.0000
   8.750   1.3426   0.04407   0.03227  -0.0675   0.2069   1.0000
   9.000   1.3550   0.04603   0.03457  -0.0663   0.2022   1.0000
   9.250   1.3741   0.04731   0.03589  -0.0655   0.1987   1.0000
   9.500   1.3783   0.05005   0.03904  -0.0640   0.1945   1.0000
   9.750   1.3837   0.05257   0.04185  -0.0625   0.1907   1.0000
  10.000   1.3962   0.05434   0.04374  -0.0614   0.1877   1.0000
  10.250   1.4155   0.05556   0.04496  -0.0607   0.1853   1.0000
  10.500   1.3894   0.06078   0.05070  -0.0582   0.1824   1.0000
  10.750   1.3507   0.06655   0.05682  -0.0556   0.1802   1.0000
  11.000   1.1992   0.08942   0.08006  -0.0647   0.1771   1.0000
  11.250   1.1611   0.10150   0.09221  -0.0713   0.1735   1.0000
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