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MA409 (smoothed) (ma409sm-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: MA409 (smoothed) (ma409sm-il)
Reynolds number: 100,000
Max Cl/Cd: 62.45 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ma409sm-il-100000-n5.txt
Download as CSV file: xf-ma409sm-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MA409 (smoothed)                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4249   0.11017   0.10490  -0.0222   1.0000   0.0465
  -9.000  -0.4249   0.10743   0.10222  -0.0242   1.0000   0.0498
  -8.750  -0.4315   0.10525   0.10018  -0.0278   1.0000   0.0512
  -8.500  -0.3406   0.08854   0.08374  -0.0299   1.0000   0.0367
  -8.250  -0.3410   0.08490   0.08015  -0.0297   1.0000   0.0347
  -8.000  -0.4220   0.09293   0.08791  -0.0269   1.0000   0.0364
  -7.750  -0.4241   0.08983   0.08487  -0.0265   1.0000   0.0342
  -7.500  -0.4300   0.08663   0.08176  -0.0265   1.0000   0.0324
  -7.000  -0.4337   0.07638   0.07164  -0.0344   1.0000   0.0276
  -6.750  -0.4305   0.07250   0.06779  -0.0361   1.0000   0.0272
  -6.500  -0.4249   0.06823   0.06354  -0.0386   1.0000   0.0268
  -6.250  -0.4163   0.06345   0.05874  -0.0421   1.0000   0.0265
  -6.000  -0.4038   0.05793   0.05315  -0.0465   1.0000   0.0261
  -5.750  -0.3860   0.05124   0.04631  -0.0522   1.0000   0.0257
  -5.500  -0.3624   0.04311   0.03782  -0.0590   1.0000   0.0253
  -5.250  -0.3336   0.03549   0.02952  -0.0650   1.0000   0.0252
  -5.000  -0.3032   0.02998   0.02320  -0.0686   1.0000   0.0257
  -4.750  -0.2731   0.02638   0.01884  -0.0704   1.0000   0.0269
  -4.500  -0.2448   0.02404   0.01604  -0.0715   1.0000   0.0298
  -4.250  -0.2178   0.02260   0.01435  -0.0720   1.0000   0.0326
  -4.000  -0.1885   0.02092   0.01231  -0.0725   1.0000   0.0352
  -3.750  -0.1591   0.01958   0.01058  -0.0728   1.0000   0.0385
  -3.500  -0.1309   0.01866   0.00962  -0.0733   1.0000   0.0460
  -3.250  -0.1017   0.01776   0.00857  -0.0738   1.0000   0.0548
  -3.000  -0.0736   0.01716   0.00795  -0.0741   1.0000   0.0702
  -2.750  -0.0452   0.01660   0.00735  -0.0745   1.0000   0.0914
  -2.500  -0.0177   0.01620   0.00702  -0.0748   1.0000   0.1231
  -2.250   0.0190   0.01589   0.00677  -0.0770   0.9961   0.1639
  -2.000   0.0555   0.01564   0.00660  -0.0791   0.9920   0.2071
  -1.750   0.0918   0.01542   0.00648  -0.0812   0.9871   0.2534
  -1.500   0.1303   0.01523   0.00638  -0.0837   0.9828   0.3066
  -1.250   0.1646   0.01502   0.00630  -0.0852   0.9759   0.3643
  -1.000   0.2032   0.01478   0.00623  -0.0876   0.9707   0.4359
  -0.750   0.2367   0.01441   0.00616  -0.0888   0.9634   0.5295
  -0.500   0.2651   0.01329   0.00602  -0.0880   0.9568   1.0000
  -0.250   0.2981   0.01334   0.00591  -0.0890   0.9475   1.0000
   0.000   0.3343   0.01337   0.00582  -0.0907   0.9400   1.0000
   0.250   0.3696   0.01339   0.00574  -0.0922   0.9318   1.0000
   0.500   0.4026   0.01340   0.00569  -0.0931   0.9225   1.0000
   0.750   0.4404   0.01335   0.00559  -0.0949   0.9155   1.0000
   1.000   0.4716   0.01333   0.00555  -0.0954   0.9046   1.0000
   1.250   0.5029   0.01330   0.00553  -0.0958   0.8933   1.0000
   1.500   0.5347   0.01324   0.00549  -0.0963   0.8815   1.0000
   1.750   0.5663   0.01318   0.00544  -0.0966   0.8688   1.0000
   2.000   0.5975   0.01311   0.00541  -0.0969   0.8544   1.0000
   2.250   0.6287   0.01304   0.00542  -0.0970   0.8385   1.0000
   2.500   0.6605   0.01296   0.00538  -0.0973   0.8212   1.0000
   2.750   0.6900   0.01294   0.00541  -0.0971   0.7998   1.0000
   3.000   0.7205   0.01291   0.00542  -0.0970   0.7766   1.0000
   3.250   0.7499   0.01294   0.00553  -0.0967   0.7495   1.0000
   3.500   0.7784   0.01303   0.00564  -0.0962   0.7185   1.0000
   3.750   0.8063   0.01318   0.00578  -0.0956   0.6841   1.0000
   4.000   0.8327   0.01342   0.00600  -0.0948   0.6459   1.0000
   4.250   0.8580   0.01374   0.00627  -0.0938   0.6047   1.0000
   4.500   0.8796   0.01428   0.00657  -0.0920   0.5350   1.0000
   4.750   0.8962   0.01520   0.00690  -0.0896   0.4310   1.0000
   5.000   0.9135   0.01619   0.00742  -0.0877   0.3333   1.0000
   5.250   0.9295   0.01755   0.00812  -0.0859   0.2145   1.0000
   5.500   0.9432   0.01956   0.00926  -0.0840   0.0846   1.0000
   5.750   0.9608   0.02113   0.01056  -0.0824   0.0512   1.0000
   6.250   0.9991   0.02362   0.01335  -0.0793   0.0366   1.0000
   6.500   1.0167   0.02498   0.01476  -0.0778   0.0314   1.0000
   6.750   1.0342   0.02647   0.01639  -0.0760   0.0291   1.0000
   7.000   1.0531   0.02802   0.01811  -0.0744   0.0274   1.0000
   7.250   1.0731   0.02980   0.02003  -0.0729   0.0260   1.0000
   7.500   1.0944   0.03179   0.02220  -0.0717   0.0248   1.0000
   7.750   1.1155   0.03386   0.02451  -0.0705   0.0234   1.0000
   8.000   1.1335   0.03621   0.02696  -0.0695   0.0214   1.0000
   8.250   1.1512   0.03895   0.03005  -0.0680   0.0199   1.0000
   8.500   1.1675   0.04179   0.03334  -0.0662   0.0194   1.0000
   8.750   1.1799   0.04498   0.03701  -0.0640   0.0190   1.0000
   9.000   1.1879   0.04845   0.04096  -0.0615   0.0187   1.0000
   9.250   1.1915   0.05213   0.04511  -0.0588   0.0185   1.0000
   9.500   1.1903   0.05595   0.04936  -0.0559   0.0184   1.0000
   9.750   1.1843   0.05984   0.05364  -0.0529   0.0183   1.0000
  10.000   1.1731   0.06357   0.05771  -0.0497   0.0183   1.0000
  10.250   1.1573   0.06723   0.06163  -0.0467   0.0183   1.0000
  10.500   1.1395   0.07118   0.06582  -0.0446   0.0184   1.0000
  10.750   1.1202   0.07565   0.07052  -0.0438   0.0185   1.0000
  11.000   1.1000   0.08082   0.07589  -0.0447   0.0186   1.0000
  11.250   1.0795   0.08689   0.08213  -0.0473   0.0187   1.0000
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