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FX 84-W-127 (fx84w127-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: FX 84-W-127 (fx84w127-il)
Reynolds number: 100,000
Max Cl/Cd: 53.82 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx84w127-il-100000.txt
Download as CSV file: xf-fx84w127-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 84-W-127                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3581   0.10407   0.09977  -0.0351   1.0000   0.1142
  -8.750  -0.3770   0.10328   0.09907  -0.0326   1.0000   0.1162
  -8.500  -0.4020   0.10131   0.09720  -0.0381   0.9957   0.1196
  -8.250  -0.3892   0.09573   0.09164  -0.0422   0.9902   0.1224
  -8.000  -0.3583   0.09204   0.08788  -0.0430   0.9865   0.1273
  -7.750  -0.3675   0.08798   0.08387  -0.0528   0.9754   0.1341
  -7.500  -0.3647   0.08215   0.07802  -0.0604   0.9663   0.1375
  -7.250  -0.3353   0.07945   0.07530  -0.0592   0.9625   0.1431
  -7.000  -0.3528   0.07329   0.06898  -0.0719   0.9482   0.1520
  -6.750  -0.3145   0.07086   0.06662  -0.0699   0.9461   0.1605
  -6.500  -0.3175   0.06672   0.06238  -0.0741   0.9356   0.1696
  -6.250  -0.2998   0.06261   0.05810  -0.0793   0.9297   0.1842
  -6.000  -0.3115   0.04927   0.04377  -0.0845   0.9177   0.1093
  -5.750  -0.2951   0.04126   0.03474  -0.0858   0.9119   0.0872
  -5.500  -0.2806   0.03840   0.03142  -0.0848   0.9040   0.0871
  -5.250  -0.2459   0.03543   0.02774  -0.0868   0.9001   0.0899
  -5.000  -0.2316   0.03388   0.02571  -0.0847   0.8917   0.0910
  -4.750  -0.1987   0.03167   0.02337  -0.0864   0.8871   0.0960
  -4.500  -0.1556   0.03011   0.02142  -0.0891   0.8841   0.1034
  -4.250  -0.1448   0.02928   0.02037  -0.0863   0.8749   0.1072
  -4.000  -0.1060   0.02821   0.01922  -0.0883   0.8708   0.1180
  -3.500  -0.0546   0.02667   0.01760  -0.0878   0.8580   0.1395
  -3.250  -0.0170   0.02577   0.01677  -0.0894   0.8543   0.1593
  -3.000  -0.0015   0.02551   0.01656  -0.0875   0.8460   0.1772
  -2.750   0.0287   0.02481   0.01602  -0.0879   0.8408   0.2137
  -2.500   0.0629   0.02366   0.01539  -0.0889   0.8375   0.2914
  -2.250   0.0663   0.02308   0.01568  -0.0854   0.8278   0.4344
  -2.000   0.0810   0.02228   0.01613  -0.0804   0.8236   0.7626
  -1.750   0.0874   0.02278   0.01673  -0.0750   0.8155   0.8549
  -1.500   0.1339   0.02302   0.01686  -0.0762   0.8114   0.9345
  -1.250   0.2745   0.02273   0.01612  -0.0954   0.8134   0.9831
  -1.000   0.3592   0.02223   0.01535  -0.1062   0.8110   1.0000
  -0.750   0.3840   0.02205   0.01503  -0.1057   0.8065   1.0000
  -0.500   0.3775   0.02283   0.01576  -0.1012   0.7951   1.0000
  -0.250   0.4041   0.02266   0.01546  -0.1008   0.7910   1.0000
   0.000   0.3942   0.02355   0.01632  -0.0956   0.7795   1.0000
   0.250   0.4233   0.02338   0.01602  -0.0955   0.7757   1.0000
   0.500   0.4136   0.02435   0.01694  -0.0902   0.7642   1.0000
   0.750   0.4454   0.02417   0.01665  -0.0904   0.7606   1.0000
   1.000   0.4412   0.02520   0.01763  -0.0862   0.7495   1.0000
   1.250   0.4745   0.02503   0.01737  -0.0865   0.7457   1.0000
   1.500   0.4779   0.02606   0.01835  -0.0836   0.7354   1.0000
   1.750   0.5102   0.02597   0.01819  -0.0839   0.7312   1.0000
   2.000   0.5466   0.02572   0.01788  -0.0846   0.7284   1.0000
   2.250   0.5491   0.02698   0.01912  -0.0818   0.7169   1.0000
   2.500   0.5872   0.02663   0.01873  -0.0827   0.7142   1.0000
   2.750   0.5900   0.02803   0.02012  -0.0801   0.7027   1.0000
   3.000   0.6274   0.02768   0.01975  -0.0808   0.6997   1.0000
   3.250   0.6333   0.02899   0.02108  -0.0786   0.6886   1.0000
   3.500   0.6699   0.02863   0.02071  -0.0792   0.6851   1.0000
   3.750   0.7090   0.02814   0.02022  -0.0800   0.6823   1.0000
   4.000   0.7138   0.02954   0.02165  -0.0777   0.6706   1.0000
   4.250   0.7559   0.02882   0.02096  -0.0787   0.6683   1.0000
   5.000   0.8033   0.03128   0.02356  -0.0749   0.6416   1.0000
   5.250   0.8471   0.03033   0.02265  -0.0759   0.6389   1.0000
   5.500   0.8509   0.03190   0.02429  -0.0736   0.6271   1.0000
   5.750   0.8967   0.03072   0.02320  -0.0746   0.6242   1.0000
   6.000   0.9042   0.03199   0.02454  -0.0725   0.6128   1.0000
   6.250   0.9522   0.03057   0.02321  -0.0737   0.6094   1.0000
   6.500   0.9631   0.03156   0.02429  -0.0718   0.5985   1.0000
   6.750   1.0106   0.03015   0.02299  -0.0730   0.5944   1.0000
   7.000   1.0255   0.03083   0.02378  -0.0713   0.5839   1.0000
   7.250   1.0746   0.02925   0.02232  -0.0726   0.5788   1.0000
   7.500   1.0946   0.02940   0.02259  -0.0712   0.5675   1.0000
   7.750   1.1378   0.02750   0.02075  -0.0713   0.5553   1.0000
   8.000   1.1751   0.02573   0.01903  -0.0707   0.5387   1.0000
   8.250   1.2052   0.02471   0.01805  -0.0697   0.5217   1.0000
   8.500   1.2315   0.02405   0.01743  -0.0684   0.5039   1.0000
   8.750   1.2538   0.02363   0.01705  -0.0668   0.4847   1.0000
   9.000   1.2645   0.02376   0.01731  -0.0639   0.4631   1.0000
   9.250   1.2778   0.02374   0.01730  -0.0612   0.4391   1.0000
   9.500   1.2826   0.02411   0.01770  -0.0576   0.4121   1.0000
   9.750   1.2796   0.02477   0.01833  -0.0531   0.3826   1.0000
  10.000   1.2722   0.02588   0.01935  -0.0486   0.3465   1.0000
  10.250   1.2598   0.02762   0.02086  -0.0442   0.2998   1.0000
  10.500   1.2411   0.03020   0.02303  -0.0401   0.2472   1.0000
  10.750   1.2198   0.03350   0.02590  -0.0365   0.1980   1.0000
  11.000   1.2009   0.03705   0.02905  -0.0338   0.1626   1.0000
  11.250   1.1891   0.04031   0.03205  -0.0316   0.1373   1.0000
  11.500   1.1828   0.04322   0.03473  -0.0298   0.1210   1.0000
  11.750   1.1837   0.04562   0.03699  -0.0283   0.1078   1.0000
  12.000   1.1901   0.04764   0.03898  -0.0269   0.0972   1.0000
  12.250   1.2030   0.04930   0.04060  -0.0255   0.0884   1.0000
  12.500   1.2228   0.05072   0.04185  -0.0244   0.0804   1.0000
  12.750   1.2400   0.05235   0.04361  -0.0234   0.0748   1.0000
  13.000   1.2739   0.05378   0.04494  -0.0227   0.0686   1.0000
  13.250   1.2869   0.05588   0.04729  -0.0219   0.0651   1.0000
  13.500   1.3077   0.05793   0.04945  -0.0213   0.0618   1.0000
  13.750   1.3450   0.06098   0.05252  -0.0214   0.0582   1.0000
  14.000   1.3401   0.06390   0.05580  -0.0201   0.0570   1.0000
  14.250   1.3366   0.06720   0.05943  -0.0191   0.0557   1.0000
  14.500   1.3319   0.07080   0.06335  -0.0184   0.0547   1.0000
  14.750   1.3246   0.07483   0.06769  -0.0179   0.0541   1.0000
  15.000   1.3131   0.07927   0.07244  -0.0177   0.0538   1.0000
  15.250   1.2975   0.08418   0.07765  -0.0179   0.0537   1.0000
  15.500   1.2778   0.08964   0.08341  -0.0188   0.0538   1.0000
  15.750   1.2550   0.09570   0.08976  -0.0203   0.0541   1.0000
  16.000   1.2294   0.10248   0.09681  -0.0227   0.0544   1.0000
  16.250   1.2019   0.11007   0.10465  -0.0260   0.0550   1.0000
  16.500   1.1722   0.11862   0.11341  -0.0305   0.0557   1.0000
  16.750   1.1411   0.12826   0.12324  -0.0361   0.0565   1.0000
  17.000   1.1110   0.13884   0.13396  -0.0426   0.0574   1.0000
  17.250   1.0884   0.14899   0.14419  -0.0486   0.0583   1.0000
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