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WORTMANN FX M2 AIRFOIL (fxm2-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX M2 AIRFOIL (fxm2-il)
Reynolds number: 50,000
Max Cl/Cd: 31.62 at α=2°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fxm2-il-50000.txt
Download as CSV file: xf-fxm2-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.2840   0.10373   0.09725  -0.0145   1.0000   0.1251
  -7.250  -0.2957   0.10368   0.09737  -0.0148   1.0000   0.1274
  -7.000  -0.3061   0.10429   0.09812  -0.0192   1.0000   0.1285
  -6.750  -0.2827   0.09653   0.09039  -0.0125   1.0000   0.1349
  -6.500  -0.2813   0.09438   0.08835  -0.0124   1.0000   0.1405
  -6.250  -0.2873   0.09407   0.08818  -0.0165   1.0000   0.1449
  -6.000  -0.2821   0.09014   0.08437  -0.0151   1.0000   0.1484
  -5.750  -0.2742   0.08691   0.08122  -0.0124   1.0000   0.1560
  -5.500  -0.2737   0.08699   0.08134  -0.0216   1.0000   0.1634
  -5.000  -0.2598   0.08125   0.07576  -0.0224   1.0000   0.1809
  -4.750  -0.2574   0.07674   0.07143  -0.0138   1.0000   0.1878
  -4.500  -0.2502   0.07438   0.06914  -0.0166   1.0000   0.2004
  -4.250  -0.2428   0.07190   0.06674  -0.0172   1.0000   0.2158
  -4.000  -0.2376   0.06927   0.06423  -0.0151   1.0000   0.2315
  -3.750  -0.2284   0.06711   0.06212  -0.0167   1.0000   0.2548
  -3.500  -0.2242   0.06471   0.05984  -0.0144   1.0000   0.2792
  -3.250  -0.2219   0.06246   0.05773  -0.0111   1.0000   0.3049
  -3.000   0.0785   0.04055   0.03546  -0.0047   1.0000   0.9722
  -2.750   0.0256   0.04244   0.03763   0.0081   1.0000   0.9377
  -2.500  -0.0226   0.04377   0.03923   0.0187   1.0000   0.9033
  -2.250  -0.0627   0.04452   0.04023   0.0271   1.0000   0.8824
  -2.000  -0.0992   0.04496   0.04091   0.0343   1.0000   0.8661
  -1.750  -0.1267   0.04496   0.04113   0.0398   1.0000   0.8645
  -1.500  -0.2330   0.05005   0.04646   0.0341   0.9768   0.6705
  -1.000   0.2358   0.03471   0.02798  -0.0844   0.9179   0.2393
  -0.750   0.3275   0.03138   0.02380  -0.0938   0.8934   0.1935
  -0.500   0.3976   0.02879   0.02066  -0.0986   0.8612   0.1730
  -0.250   0.4608   0.02647   0.01792  -0.1017   0.8254   0.1693
   0.000   0.5123   0.02472   0.01572  -0.1023   0.7834   0.1678
   0.250   0.5507   0.02372   0.01427  -0.1011   0.7365   0.1683
   0.500   0.5818   0.02326   0.01342  -0.0993   0.6912   0.1758
   0.750   0.6105   0.02310   0.01293  -0.0978   0.6506   0.1843
   1.000   0.6383   0.02317   0.01276  -0.0965   0.6143   0.1949
   1.250   0.6673   0.02330   0.01279  -0.0958   0.5846   0.2203
   1.500   0.6849   0.02179   0.01310  -0.0929   0.5607   1.0000
   1.750   0.7138   0.02260   0.01324  -0.0917   0.5394   1.0000
   2.000   0.7416   0.02345   0.01355  -0.0908   0.5203   1.0000
   2.250   0.7673   0.02433   0.01413  -0.0900   0.5016   1.0000
   2.500   0.7936   0.02518   0.01468  -0.0894   0.4857   1.0000
   2.750   0.8203   0.02608   0.01529  -0.0888   0.4720   1.0000
   3.000   0.8456   0.02715   0.01626  -0.0884   0.4594   1.0000
   3.250   0.8702   0.02836   0.01744  -0.0880   0.4481   1.0000
   3.500   0.8952   0.02950   0.01851  -0.0875   0.4382   1.0000
   3.750   0.9209   0.03053   0.01938  -0.0870   0.4285   1.0000
   4.000   0.9434   0.03189   0.02080  -0.0865   0.4185   1.0000
   4.250   0.9682   0.03310   0.02192  -0.0860   0.4103   1.0000
   4.500   0.9905   0.03451   0.02338  -0.0854   0.4012   1.0000
   4.750   1.0114   0.03612   0.02510  -0.0848   0.3928   1.0000
   5.000   1.0351   0.03743   0.02637  -0.0842   0.3851   1.0000
   5.250   1.0521   0.03950   0.02867  -0.0835   0.3771   1.0000
   5.500   1.0783   0.04047   0.02947  -0.0829   0.3694   1.0000
   5.750   1.0909   0.04301   0.03233  -0.0821   0.3611   1.0000
   6.000   1.1121   0.04464   0.03400  -0.0814   0.3537   1.0000
   6.250   1.1292   0.04656   0.03601  -0.0805   0.3448   1.0000
   6.500   1.1393   0.04922   0.03888  -0.0795   0.3356   1.0000
   6.750   1.1592   0.05060   0.04024  -0.0785   0.3262   1.0000
   7.000   1.1763   0.05237   0.04208  -0.0775   0.3177   1.0000
   7.250   1.1708   0.05709   0.04715  -0.0766   0.3115   1.0000
   7.500   1.1890   0.05901   0.04914  -0.0758   0.3051   1.0000
   7.750   1.1695   0.06556   0.05601  -0.0754   0.3015   1.0000
   8.000   1.1081   0.07707   0.06779  -0.0771   0.3015   1.0000
   8.250   1.0555   0.08830   0.07911  -0.0809   0.3039   1.0000
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