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FX 77-W-121 (fx77w121-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: FX 77-W-121 (fx77w121-il)
Reynolds number: 100,000
Max Cl/Cd: 19 at α=2°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx77w121-il-100000.txt
Download as CSV file: xf-fx77w121-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 77-W-121                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2870   0.10973   0.10482  -0.0259   0.7112   0.0703
  -9.250  -0.2923   0.10821   0.10333  -0.0303   0.7048   0.0711
  -9.000  -0.2948   0.10585   0.10098  -0.0338   0.6991   0.0714
  -8.750  -0.2704   0.09927   0.09433  -0.0306   0.6911   0.0742
  -8.500  -0.2585   0.09617   0.09117  -0.0303   0.6854   0.0777
  -8.250  -0.2547   0.09331   0.08833  -0.0317   0.6800   0.0809
  -8.000  -0.2568   0.09085   0.08590  -0.0342   0.6757   0.0838
  -7.750  -0.2737   0.08909   0.08418  -0.0390   0.6730   0.0855
  -7.500  -0.2830   0.08704   0.08211  -0.0436   0.6695   0.0860
  -7.250  -0.2622   0.08134   0.07647  -0.0397   0.6642   0.0891
  -7.000  -0.2520   0.07845   0.07355  -0.0392   0.6602   0.0924
  -6.750  -0.2480   0.07571   0.07074  -0.0408   0.6570   0.0958
  -6.500  -0.2613   0.07449   0.06924  -0.0484   0.6546   0.1010
  -6.250  -0.2426   0.06890   0.06388  -0.0457   0.6506   0.1040
  -6.000  -0.2298   0.06632   0.06127  -0.0451   0.6474   0.1086
  -5.750  -0.2277   0.06363   0.05825  -0.0488   0.6453   0.1169
  -5.500  -0.2112   0.06028   0.05501  -0.0469   0.6426   0.1214
  -5.250  -0.2020   0.05765   0.05215  -0.0485   0.6398   0.1326
  -5.000  -0.1852   0.05499   0.04959  -0.0475   0.6364   0.1392
  -4.750  -0.1720   0.05246   0.04693  -0.0474   0.6335   0.1513
  -4.500  -0.1575   0.05025   0.04462  -0.0467   0.6308   0.1676
  -4.250  -0.1448   0.04838   0.04255  -0.0460   0.6287   0.1935
  -4.000  -0.1284   0.04620   0.04041  -0.0447   0.6265   0.2128
  -3.750  -0.1136   0.04446   0.03865  -0.0437   0.6241   0.2404
  -3.500  -0.0985   0.04271   0.03696  -0.0420   0.6217   0.2724
  -3.250  -0.0482   0.03442   0.02615  -0.0426   0.6200   0.0850
  -3.000  -0.0252   0.03251   0.02388  -0.0414   0.6176   0.0845
  -2.750  -0.0007   0.03079   0.02175  -0.0402   0.6153   0.0844
  -2.500   0.0253   0.02927   0.01987  -0.0393   0.6132   0.0837
  -2.250   0.0519   0.02844   0.01877  -0.0388   0.6108   0.0856
  -2.000   0.0782   0.02736   0.01769  -0.0390   0.6086   0.0922
  -1.750   0.1058   0.02670   0.01696  -0.0389   0.6064   0.0968
  -1.500   0.1324   0.02608   0.01634  -0.0387   0.6040   0.1050
  -1.250   0.3000   0.02096   0.01400  -0.0650   0.5996   1.0000
  -1.000   0.3237   0.02143   0.01414  -0.0644   0.5977   1.0000
  -0.750   0.3471   0.02213   0.01471  -0.0645   0.5955   1.0000
  -0.500   0.3704   0.02286   0.01531  -0.0646   0.5935   1.0000
  -0.250   0.3933   0.02356   0.01587  -0.0644   0.5909   1.0000
   0.000   0.4160   0.02416   0.01634  -0.0640   0.5883   1.0000
   0.250   0.4388   0.02474   0.01676  -0.0634   0.5861   1.0000
   0.500   0.4616   0.02536   0.01725  -0.0628   0.5845   1.0000
   0.750   0.4832   0.02627   0.01808  -0.0626   0.5823   1.0000
   1.000   0.5023   0.02766   0.01952  -0.0630   0.5789   1.0000
   1.250   0.5218   0.02886   0.02069  -0.0630   0.5760   1.0000
   1.500   0.5423   0.02973   0.02149  -0.0625   0.5730   1.0000
   1.750   0.5641   0.03037   0.02204  -0.0616   0.5706   1.0000
   2.000   0.5870   0.03090   0.02247  -0.0606   0.5687   1.0000
   2.250   0.5947   0.03370   0.02540  -0.0614   0.5646   1.0000
   2.500   0.6048   0.03584   0.02758  -0.0614   0.5608   1.0000
   2.750   0.6204   0.03721   0.02894  -0.0607   0.5578   1.0000
   3.000   0.6438   0.03766   0.02931  -0.0595   0.5552   1.0000
   3.250   0.6455   0.04050   0.03220  -0.0591   0.5506   1.0000
   3.500   0.6312   0.04455   0.03633  -0.0587   0.5461   1.0000
   3.750   0.6563   0.04485   0.03658  -0.0575   0.5417   1.0000
   4.000   0.7010   0.04338   0.03501  -0.0560   0.5390   1.0000
   4.250   0.5561   0.05740   0.04920  -0.0537   0.5578   1.0000
   4.500   0.5710   0.05922   0.05100  -0.0532   0.5559   1.0000
   4.750   0.5900   0.06113   0.05291  -0.0530   0.5545   1.0000
   5.000   0.6298   0.05818   0.04987  -0.0496   0.5192   1.0000
   5.250   0.6208   0.06117   0.05286  -0.0484   0.5162   1.0000
   5.750   0.6205   0.06673   0.05844  -0.0473   0.5137   1.0000
   6.000   0.6294   0.06908   0.06083  -0.0471   0.5120   1.0000
   6.250   0.6826   0.06574   0.05744  -0.0442   0.4832   1.0000
   6.500   0.6985   0.06689   0.05860  -0.0432   0.4752   1.0000
   6.750   0.7106   0.06830   0.06004  -0.0424   0.4678   1.0000
   7.000   0.7165   0.07013   0.06191  -0.0414   0.4589   1.0000
   7.250   0.7368   0.07105   0.06286  -0.0406   0.4527   1.0000
   7.500   0.7965   0.06901   0.06089  -0.0395   0.4494   1.0000
   7.750   0.7550   0.07466   0.06654  -0.0392   0.4381   1.0000
   8.000   0.8072   0.07301   0.06499  -0.0379   0.4345   1.0000
   8.250   0.7817   0.07739   0.06938  -0.0377   0.4228   1.0000
   8.500   0.8231   0.07662   0.06870  -0.0365   0.4195   1.0000
   8.750   0.7932   0.08180   0.07389  -0.0369   0.4086   1.0000
   9.000   0.8258   0.08164   0.07381  -0.0357   0.4040   1.0000
   9.250   0.8120   0.08548   0.07769  -0.0359   0.3941   1.0000
   9.500   0.8343   0.08625   0.07856  -0.0350   0.3889   1.0000
   9.750   0.8231   0.09023   0.08258  -0.0355   0.3807   1.0000
  10.000   0.8506   0.09026   0.08271  -0.0344   0.3752   1.0000
  10.250   0.8375   0.09466   0.08715  -0.0351   0.3674   1.0000
  10.500   0.8779   0.09336   0.08599  -0.0335   0.3640   1.0000
  10.750   0.8511   0.09928   0.09193  -0.0348   0.3541   1.0000
  11.000   0.8900   0.09801   0.09080  -0.0332   0.3506   1.0000
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